Subject: NASA Turbo compound rotary
From: Rotary Engine
Date: 3/13/2006, 11:27 AM
To: AAme


paul,
interesting article.  worth your sifting through.
a comment and a few questions:

comment:
they obviously thought it important to be able to separate the power
turbine from the turbo for speed optimization reasons.  you're gonna
have a lot of guess and try having them coupled.

questions:
1. it's unclear to me what the base rotary engine is in this study,  do
you know?

2. the delta hp therefore is confusing.  when they say the power turbine
is capable of 40hp min and up to 80hp, what is the size of the engine in
my item i. to produce this? and what % increase is this in both power
output and weight?

3.  206 lbm system weight?  what is this?  and what is included.

good find.
tell me what you assess after you go through it thoroughly.

steve

1) No I don't. Probably one of the CW, John Deere or RPI versions.
We are comeing up with the same sort of numbers for the Mazda.

2) Your guess is as good as mine on the exact engine configuration
as there were so many. CW, John Deere and RPI had many mechanical problems
that Mazda solved years ago.

Here is a list of back ground NASA papers so you can choose an engine
from one of these.

Most of these papers are available from in pdf form:

http://ntrs.nasa.gov/index.cgi?method=search&limit=25&offset=0&mode=simple&order=DESC&keywords=rotary+engines


Paul Lamar
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1.     Advanced Propulsion Systems Study for General Aviation Aircraft
Mount, R.
NASA Center for AeroSpace Information (CASI)
NASA/CR-2003-212334; NAS 1.26:212334; E-13929 , 20030701; July 2003
This study defines a family of advanced technology Stratified Charge Rotary Engines (SCRE) appropriate for the enablement of the development of a new generation of general aviation aircraft. High commonality, affordability, and environmental compatibility are considerations influencing the family composition and ratings. The SCRE family is comprised of three engines in the 70 Series (40 cu in. displacement per rotor), i.e. one, two, and four rotor and two engines in the 170 Series (105 cu in. displacement per rotor), i.e., two and four rotor. The two rotor engines are considered the primary engines in each series. A wide power range is considered covering 125 to 2500 HP through growth and compounding/dual pac considerations. Mission requirements, TBO, FAA Certification, engine development cycles, and costs are examined. Comparisons to current and projected reciprocating and turbine engine configurations in the 125 to 1000 HP class are provided. Market impact, estimated sales, and U.S. job creation (R&D, manufacturing and infractures) are examined.
Document ID: 20030062917
View PDF File
Updated/Added to NTRS: 2005-08-25
2.     A Powerful New Engine

NASA Center for AeroSpace Information (CASI)
Spinoff 2001: Special Millennium Feature, NASA/NP-2001-04-264-HQ, 67 , 20010101; 2001
Through Small Business Innovation Research (SBIR) funding from NASA's Glenn Research Center, Moller International created a new coating for rotary engines, which significantly improves the fuel consumption of a vehicle while reducing emissions. The new coatings are offered in the new Rotapower(R) engine, which is produced and distributed by Moller subsidiary, Freedom Motors, Inc. The coating allows the Rotapower engine to function smoother than other models, reducing wear and protecting the engine. The Rotapower engine has the ability to operate on a variety of fuels, including gasoline, natural gas, diesel, alcohol, and kerosene. A small and lightweight engine, it is projected to replace many of today's bulkier versions. The 10 horsepower model fits in the palm of one's hand, while the 160 horsepower model fits into a 5-gallon bucket. The clean running Rotapower engine is environmentally appealing, because it eliminates over 98 percent of the total emissions given off by traditional piston engines. Fewer pollutants are spewed into the air, making it especially attractive in areas where air pollution is a major problem. Due to the clean-burning nature of the engine, it meets the stringent standards set by the California Air Resources Board. The engine also has numerous commercial benefits in several types of recreational, industrial, and transportation applications, including personal watercraft, snowmobiles, portable generators. and pumps.
Document ID: 20020062174
No Digital Version Available - Order This Document from CASI
Updated/Added to NTRS: 2004-11-03

6
7.     Evaluation of thermal barrier and PS-200 self-lubricating coatings in an air-cooled rotary engine
Moller, Paul S.
NASA Center for AeroSpace Information (CASI)
NASA-CR-195445; E-9493; NAS 1.26:195445 , 19950301; Mar 1, 1995
This project provides an evaluation of the feasibility and desirability of applying a thermal barrier coating overlaid with a wear coating on the internal surfaces of the combustion area of rotary engines. Many experiments were conducted with different combinations of coatings applied to engine components of aluminum, iron and titanium, and the engines were run on a well-instrumented test stand. Significant improvements in specific fuel consumption were achieved and the wear coating, PS-200, which was invented at NASA's Lewis Research Center, held up well under severe test conditions.
Accession ID: 95N23222
Document ID: 19950016805
View PDF File
Updated/Added to NTRS: 2005-08-25


10.     Rotary engine performance limits predicted by a zero-dimensional model
Bartrand, Timothy A.; Willis, Edward A.
NASA Center for AeroSpace Information (CASI)
NASA-CR-189129; E-6880; NAS 1.26:189129; International Congress and Exposition, Detroit, MI, United States, 24-28 Feb. 1992 , 19920301; Mar 1, 1992
A parametric study was performed to determine the performance limits of a rotary combustion engine. This study shows how well increasing the combustion rate, insulating, and turbocharging increase brake power and decrease fuel consumption. Several generalizations can be made from the findings. First, it was shown that the fastest combustion rate is not necessarily the best combustion rate. Second, several engine insulation schemes were employed for a turbocharged engine. Performance improved only for a highly insulated engine. Finally, the variability of turbocompounding and the influence of exhaust port shape were calculated. Rotary engines performance was predicted by an improved zero-dimensional computer model based on a model developed at the Massachusetts Institute of Technology in the 1980's. Independent variables in the study include turbocharging, manifold pressures, wall thermal properties, leakage area, and exhaust port geometry. Additions to the computer programs since its results were last published include turbocharging, manifold modeling, and improved friction power loss calculation. The baseline engine for this study is a single rotor 650 cc direct-injection stratified-charge engine with aluminum housings and a stainless steel rotor. Engine maps are provided for the baseline and turbocharged versions of the engine.
Accession ID: 92N20650
Document ID: 19920011408
View PDF File
Updated/Added to NTRS: 2005-08-25

12.     Rotary engine technology
Willis, Edward A.; Mcfadden, John J.
NASA Center for AeroSpace Information (CASI)
Aeropropulsion 1991, 11 p , 19910301; Mar 1, 1991
The original goal in this program was to combine some of the better features of reciprocating and gas-turbine engines; thus, obtaining a superior powerplant for light aircraft and a host of related uses. Based on a series of engine and aircraft/mission studies conducted in the early 1980's, the rotary (Wankel) engine was perceived to have many of the desired features and was judged to be capable of considerable further development. At the time, existing automotive rotary engines had demonstratably high power outputs in a compact, smooth-running, and reliable package but were less fuel efficient than comparable reciprocating engines. Accordingly, the basic thrust of the NASA Rotary Engine Technology Enablement Program was (and is) to bring the rotary's efficiency up to the level of a comparably sized diesel, without sacrificing its other desirable features.
Accession ID: 91N20114
Document ID: 19910010801
No Digital Version Available - Order This Document from CASI
Updated/Added to NTRS: 2004-11-03


14.     Performance of a supercharged direct-injection stratified-charge rotary combustion engine
Bartrand, Timothy A.; Willis, Edward A.
NASA Center for AeroSpace Information (CASI)
NASA-TM-103105; E-5430; NAS 1.15:103105; Joint Symposium on General Aviation Systems, Ocean City, NJ, United States, 11-12 Apr. 1990 , 19900401; Apr 1, 1990
A zero-dimensional thermodynamic performance computer model for direct-injection stratified-charge rotary combustion engines was modified and run for a single rotor supercharged engine. Operating conditions for the computer runs were a single boost pressure and a matrix of speeds, loads and engine materials. A representative engine map is presented showing the predicted range of efficient operation. After discussion of the engine map, a number of engine features are analyzed individually. These features are: heat transfer and the influence insulating materials have on engine performance and exhaust energy; intake manifold pressure oscillations and interactions with the combustion chamber; and performance losses and seal friction. Finally, code running times and convergence data are presented.
Accession ID: 90N25982
Document ID: 19900016666
View PDF File
Updated/Added to NTRS: 2005-08-25



17.     Fuel-air mixing and distribution in a direct-injection stratified-charge rotary engine
Abraham, J.; Bracco, F. V.
NASA Center for AeroSpace Information (CASI)
SAE PAPER 890329; International Congress and Exposition on Rotary Engine Design: Analysis and Developments, Detroit, MI, United States, Feb. 27-Mar. 3, 1989 , 19890101; JAN 1, 1989
A three-dimensional model for flows and combustion in reciprocating and rotary engines is applied to a direct-injection stratified-charge rotary engine to identify the main parameters that control its burning rate. It is concluded that the orientation of the six sprays of the main injector with respect to the air stream is important to enhance vaporization and the production of flammable mixture. In particular, no spray should be in the wake of any other spray. It was predicted that if such a condition is respected, the indicated efficiency would increase by some 6 percent at higher loads and 2 percent at lower loads. The computations led to the design of a new injector tip that has since yielded slightly better efficiency gains than predicted.
Accession ID: 89A51491
Document ID: 19890064120
No Digital Version Available - Go to Tips on Ordering
Updated/Added to NTRS: 2004-11-03

18.     Strain measurements in a rotary engine housing
Lee, C. M.; Bond, T. H.; Addy, H. E.; Chun, K. S.; Lu, C. Y.
NASA Center for AeroSpace Information (CASI)
SAE PAPER 890333; International Congress and Exposition on Rotary Engine Design: Analysis and Developments, Detroit, MI, United States, Feb. 27-Mar. 3, 1989 , 19890101; JAN 1, 1989
The development of structural design tools for Rotary Combustion Engines (RCE) using Finite Element Modeling (FEM) requires knowledge about the response of engine materials to various service conditions. This paper describes experimental work that studied housing deformation as a result of thermal, pressure and mechanical loads. The measurement of thermal loads, clamping pressure, and deformation was accomplished by use of high-temperature strain gauges, thermocouples, and a high speed data acquisition system. FEM models for heat transfer stress analysis of the rotor housing will be verified and refined based on these experimental results.
Accession ID: 89A51493
Document ID: 19890064122
No Digital Version Available - Go to Tips on Ordering
Updated/Added to NTRS: 2004-11-03

19.     Regressed relations for forced convection heat transfer in a direct injection stratified charge rotary engine
Lee, Chi M.; Schock, Harold J.
NASA Center for AeroSpace Information (CASI)
SAE PAPER 880626 , 19880201; Feb 1, 1988
Currently, the heat transfer equation used in the rotary combustion engine (RCE) simulation model is taken from piston engine studies. These relations have been empirically developed by the experimental input coming from piston engines whose geometry differs considerably from that of the RCE. The objective of this work was to derive equations to estimate heat transfer coefficients in the combustion chamber of an RCE. This was accomplished by making detailed temperature and pressure measurements in a direct injection stratified charge (DISC) RCE under a range of conditions. For each specific measurement point, the local gas velocity was assumed equal to the local rotor tip speed. Local physical properties of the fluids were then calculated. Two types of correlation equations were derived and are described in this paper. The first correlation expresses the Nusselt number as a function of the Prandtl number, Reynolds number, and characteristic temperature ratio; the second correlation expresses the forced convection heat transfer coefficient as a function of fluid temperature, pressure and velocity.
Accession ID: 89A12308
Document ID: 19890024937
No Digital Version Available - Go to Tips on Ordering
Updated/Added to NTRS: 2004-11-03

19.     Regressed relations for forced convection heat transfer in a direct injection stratified charge rotary engine
Lee, Chi M.; Schock, Harold J.
NASA Center for AeroSpace Information (CASI)
SAE PAPER 880626 , 19880201; Feb 1, 1988
Currently, the heat transfer equation used in the rotary combustion engine (RCE) simulation model is taken from piston engine studies. These relations have been empirically developed by the experimental input coming from piston engines whose geometry differs considerably from that of the RCE. The objective of this work was to derive equations to estimate heat transfer coefficients in the combustion chamber of an RCE. This was accomplished by making detailed temperature and pressure measurements in a direct injection stratified charge (DISC) RCE under a range of conditions. For each specific measurement point, the local gas velocity was assumed equal to the local rotor tip speed. Local physical properties of the fluids were then calculated. Two types of correlation equations were derived and are described in this paper. The first correlation expresses the Nusselt number as a function of the Prandtl number, Reynolds number, and characteristic temperature ratio; the second correlation expresses the forced convection heat transfer coefficient as a function of fluid temperature, pressure and velocity.
Accession ID: 89A12308
Document ID: 19890024937
No Digital Version Available - Go to Tips on Ordering
Updated/Added to NTRS: 2004-11-03

20.     Regressed relations for forced convection heat transfer in a direct injection stratified charge rotary engine
Lee, Chi M.; Schock, Harold J.
NASA Center for AeroSpace Information (CASI)
NASA-TM-100124; E-3689; NAS 1.15:100124 , 19880101; JAN 1, 1988
Currently, the heat transfer equation used in the rotary combustion engine (RCE) simulation model is taken from piston engine studies. These relations have been empirically developed by the experimental input coming from piston engines whose geometry differs considerably from that of the RCE. The objective of this work was to derive equations to estimate heat transfer coefficients in the combustion chamber of an RCE. This was accomplished by making detailed temperature and pressure measurements in a direct injection stratified charge (DISC) RCE under a range of conditions. For each specific measurement point, the local gas velocity was assumed equal to the local rotor tip speed. Local physical properties of the fluids were then calculated. Two types of correlation equations were derived and are described in this paper. The first correlation expresses the Nusselt number as a function of the Prandtl number, Reynolds number, and characteristic temperature ratio; the second correlation expresses the forced convection heat transfer coefficient as a function of fluid temperature, pressure and velocity.
Accession ID: 88N13345
Document ID: 19880003963
View PDF File
Updated/Added to NTRS: 2005-08-25

21.     Performance and combustion characteristics of direct-injection stratified-charge rotary engines
Nguyen, Hung Lee
NASA Center for AeroSpace Information (CASI)
NASA-TM-100134; E-3684; NAS 1.15:100134 , 19871201; Dec 1, 1987
Computer simulations of the direct-injection stratified-charge (DISC) Wankel engine have been used to calculate heat release rates and performance and efficiency characteristics of the 1007R engine. Engine pressure data have been used in a heat release analysis to study the effects of heat transfer, leakage, and crevice flows. Predicted engine performance data are compared with experimental test data over a range of engine speeds and loads. An examination of methods to improve the performance of the Wankel engine with faster combustion, reduced leakage, higher compression ratio, and turbocharging is presented.
Accession ID: 88N12490
Document ID: 19880003108
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Updated/Added to NTRS: 2005-08-25

22.     Magnesium composite material for advanced rotary aircraft engines
Whitman, Walter R.; Goddard, David M.
NASA Center for AeroSpace Information (CASI)
NASA-CR-194229; NAS 1.26:194229; MCI-85-0458 , 19870529; May 29, 1987
Rotary engines are attractive power sources for general aviation aircraft because of their potential for high efficiency and durability, which are a result of the low number of movable parts, compactness, and extremely high horsepower to weight ratio of these engines. In order to adapt the rotary engine to aircraft use, it is essential to reduce the weight of such components as the engine housings, rotors, and crankshaft. One method of reducing weight is to employ high performance, lightweight materials. Graphite/magnesium (Gr/Mg) composites, consisting of continuous graphite fibers in a magnesium alloy matrix, possess excellent mechanical properties combined with a very low density. In addition, these materials maintain both their integrity and their properties at the operating temperatures encountered in a rotary engine, plus they offer essentially metallic thermal conductivity. This Final Report summarizes the results of a Phase II SBIR program, sponsored by NASA Lewis Research Center, on the development of cast Gr/Mg rotary engine components. In Phase I, an intermediate housing was successfully cast; this component had been selected because it represented a major, but not impossible, casting challenge. For Phase II, the target component was changed to a rotor housing, because it was determined that the performance requirements of this housing would better demonstrate the advantageous properties of Gr/Mg castings. The ultimate goal of this program was the fabrication of a cast Gr/Mg rotor housing which would perform under the service conditions of an operating rotary engine.
Accession ID: 94N70558
Document ID: 19940003803
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Updated/Added to NTRS: 2005-08-25

24.     Advanced liquid-cooled, turbocharged and intercooled stratified charge rotary engines for aircraft
Mount, Robert E.; Bartel, John; Hady, William F.
NASA Center for AeroSpace Information (CASI)
SAE PAPER 871039 , 19870401; Apr 1, 1987
Developments concerning stratified-charge rotary (SCR) engines over the past 10 years are reviewed. Aircraft engines being developed using SCR technology are shown and described, and the ability of such technology to meet general aviation engine needs is considered. Production timing and availability of SCR technology for the development of aviation rotary engines are discussed, and continuing efforts toward improving this technology, including NASA efforts, are described.
Accession ID: 87A48766
Document ID: 19870061492
No Digital Version Available - Go to Tips on Ordering
Updated/Added to NTRS: 2004-11-03

25.     Performance and efficiency evaluation and heat release study of an outboard Marine Corporation Rotary Combustion Engine
Nguyen, H. L.; Addy, H. E.; Bond, T. H.; Lee, C. M.; Chun, K. S.
NASA Center for AeroSpace Information (CASI)
NASA-TM-89833; E-3488; NAS 1.15:89833 , 19870401; Apr 1, 1987
A computer simulation which models engine performance of the Direct Injection Stratified Charge (DISC) rotary engines was used to study the effect of variations in engine design and operating parameters on engine performance and efficiency of an experimental Outboard Marine Corporation (OMC) rotary combustion engine. Engine pressure data were used in a heat release analysis to study the effects of heat transfer, leakage, and crevice flows. Predicted engine data were compared with experimental test data over a range of engine speeds and loads. An examination of methods to improve the performance of the rotary engine using advanced heat engine concepts such as faster combustion, reduced leakage, and turbocharging is also presented.
Accession ID: 87N20282
Document ID: 19870010849
View PDF File
Updated/Added to NTRS: 2005-10-13

26.     Performance and efficiency evaluation and heat release study of a direct-injection stratified-charge rotary engine
Nguyen, H. L.; Addy, H. E.; Bond, T. H.; Lee, C. M.; Chun, K. S.
NASA Center for AeroSpace Information (CASI)
SAE PAPER 870445 , 19870201; Feb 1, 1987
A computer simulation which models engine performance of the Direct Injection Stratified Charge (DISC) rotary engines was used to study the effect of variations in engine design and operating parameters on engine performance and efficiency of an Outboard Marine Corporation (OMC) experimental rotary combustion engine. Engine pressure data were used in a heat release analysis to study the effects of heat transfer, leakage, and crevice flows. Predicted engine data were compared with experimental test data over a range of engine speeds and loads. An examination of methods to improve the performance of the rotary engine using advanced heat engine concepts such as faster combustion, reduced leakage, and turbocharging is also presented.
Accession ID: 88A23313
Document ID: 19880036086
No Digital Version Available - Go to Tips on Ordering
Updated/Added to NTRS: 2004-11-03

28.     The application of cast SiC/Al to rotary engine components
Stoller, H. M.; Carluccio, J. R.; Norman, J. P.
NASA Center for AeroSpace Information (CASI)
NASA-CR-179610; NAS 1.26:179610; PDA-86-FR-5333-00-06 , 19860815; Aug 15, 1986
A silicon carbide reinforced aluminum (SiC/Al) material fabricated by Dural Aluminum Composites Corporation was tested for various components of rotary engines. Properties investigated included hardness, high temperature strength, wear resistance, fatigue resistance, thermal conductivity, and expansion. SiC/Al appears to be a viable candidate for cast rotors, and may be applicable to other components, primarily housings.
Accession ID: 90N13385
Document ID: 19900004069
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Updated/Added to NTRS: 2005-08-25

29.     Stratified charge rotary engine for general aviation
Mount, R. E.; Parente, A. M.; Hady, W. F.
NASA Center for AeroSpace Information (CASI)
ASME PAPER 86-GT-181 , 19860601; Jun 1, 1986
A development history, a current development status assessment, and a design feature and performance capabilities account are given for stratified-charge rotary engines applicable to aircraft propulsion. Such engines are capable of operating on Jet-A fuel with substantial cost savings, improved altitude capability, and lower fuel consumption by comparison with gas turbine powerplants. Attention is given to the current development program of a 400-hp engine scheduled for initial operations in early 1990. Stratified charge rotary engines are also applicable to ground power units, airborne APUs, shipboard generators, and vehicular engines.
Accession ID: 86A48231
Document ID: 19860063493
No Digital Version Available - Go to Tips on Ordering
Updated/Added to NTRS: 2004-11-03

37.     A dynamic analysis of rotary combustion engine seals
Knoll, J.; Vilmann, C. R.; Schock, H. J.; Stumpf, R. P.
NASA Center for AeroSpace Information (CASI)
NASA-TM-83536; E-1902; NAS 1.15:83536; Ann. Congr. and Exposition, Detroit, MI, United States, 27 Feb. - 2 Mar. 1984 , 19840101; JAN 1, 1984
Real time work cell pressures are incorporated into a dynamic analysis of the gas sealing grid in Rotary Combustion Engines. The analysis which utilizes only first principal concepts accounts for apex seal separation from the crochoidal bore, apex seal shifting between the sides of its restraining channel, and apex seal rotation within the restraining channel. The results predict that apex seals do separate from the trochoidal bore and shift between the sides of their channels. The results also show that these two motions are regularly initiated by a seal rotation. The predicted motion of the apex seals compares favorably with experimental results. Frictional losses associated with the sealing grid are also calculated and compare well with measurements obtained in a similar engine. A comparison of frictional losses when using steel and carbon apex seals has also been made as well as friction losses for single and dual side sealing.
Accession ID: 84N14519
Document ID: 19840006451
No Digital Version Available - Order This Document from CASI
Updated/Added to NTRS: 2004-11-03

38.     An overview of the NASA rotary engine research program
Meng, P. R.; Hady, W. F.
NASA Center for AeroSpace Information (CASI)
NASA-TM-83699; E-2157; NAS 1.15:83699; Intern. Meeting, San Diego, CA, United States, 6-9 Aug. 1984 , 19840101; JAN 1, 1984
A brief overview and technical highlights of the research efforts and studies on rotary engines over the last several years at the NASA Lewis Research Center are presented. The test results obtained from turbocharged rotary engines and preliminary results from a high performance single rotor engine were discussed. Combustion modeling studies of the rotary engine and the use of a Laser Doppler Velocimeter to confirm the studies were examined. An in-house program in which a turbocharged rotary engine was installed in a Cessna Skymaster for ground test studies was reviewed. Details are presented on single rotor stratified charge rotary engine research efforts, both in-house and on contract.
Accession ID: 84N28791
Document ID: 19840020722
No Digital Version Available - Order This Document from CASI
Updated/Added to NTRS: 2004-11-03

39.     An overview of NASA intermittent combustion engine research
Willis, E. A.; Wintucky, W. T.
NASA Center for AeroSpace Information (CASI)
NASA-TM-83668; E-2111; NAS 1.15:83668; Joint Propulsion Conf., Cincinnati, OH, United States, 11-13 Jun. 1984 , 19840101; JAN 1, 1984
This paper overviews the current program, whose objective is to establish the generic technology base for advanced aircraft I.C. engines of the early 1990's and beyond. The major emphasis of this paper is on development of the past two years. Past studies and ongoing confirmatory experimental efforts are reviewed, which show unexpectly high potential when modern aerospace technologies are applied to inherently compact and balanced I.C. engine configurations. Currently, the program is focussed on two engine concepts the stratified-charge, multi-fuel rotary, and the lightweight two-stroke diesel. A review is given of contracted and planned high performance one-rotor and one-cylinder test engine work addressing several levels of technology. Also reviewed are basic supporting efforts, e.g., the development and experimental validation of computerized airflow and combustion process models, being performed in-house at Lewis Research Center and by university grants.
Accession ID: 84N24583
Document ID: 19840016515
No Digital Version Available - Order This Document from CASI
Updated/Added to NTRS: 2004-11-03

40.     Multi-fuel rotary engine for general aviation aircraft
Jones, C.; Ellis, D. R.; Meng, P. R.
NASA Center for AeroSpace Information (CASI)
NASA-TM-85428; NAS 1.15:85428 , 19830627; Jun 27, 1983
Design studies, conducted for NASA, of Advanced Multi-fuel General Aviation and Commuter Aircraft Rotary Stratified Charge Engines are summarized. Conceptual design studies of an advanced engine sized to provide 186/250 shaft KW/HP under cruise conditions at 7620/25,000 m/ft. altitude were performed. Relevant engine development background covering both prior and recent engine test results of the direct injected unthrottled rotary engine technology, including the capability to interchangeably operate on gasoline, diesel fuel, kerosene, or aviation jet fuel, are presented and related to growth predictions. Aircraft studies, using these resultant growth engines, define anticipated system effects of the performance and power density improvements for both single engine and twin engine airplanes. The calculated results indicate superior system performance and 30 to 35% fuel economy improvement for the Rotary-engine airplanes as compared to equivalent airframe concept designs with current baseline engines. The research and technology activities required to attain the projected engine performance levels are also discussed.
Accession ID: 83N36031
Document ID: 19830027760
No Digital Version Available - Order This Document from CASI
Updated/Added to NTRS: 2004-11-03

41.     Multi-fuel rotary engine for general aviation aircraft
Jones, C.; Ellis, D. R.; Meng, P. R.
NASA Center for AeroSpace Information (CASI)
AIAA PAPER 83-1340 , 19830601; Jun 1, 1983
Design studies of advanced multifuel general aviation and commuter aircraft rotary stratified charge engines are summarized. Conceptual design studies were performed at two levels of technology, an advanced general aviation engines sized to provide 186/250 shaft kW/hp under cruise conditions at 7620 (25,000 m/ft) altitude. A follow on study extended the results to larger (2500 hp max.) engine sizes suitable for applications such as commuter transports and helicopters. The study engine designs were derived from relevant engine development background including both prior and recent engine test results using direct injected unthrottled rotary engine technology. Aircraft studies, using these resultant growth engines, define anticipated system effects of the performance and power density improvements for both single engine and twin engine airplanes. The calculated results indicate superior system performance and 27 to 33 percent fuel economy improvement for the rotary engine airplanes as compared to equivalent airframe concept designs with current baseline engines. The research and technology activities required to attain the projected engine performance levels are also discussed. Previously announced in STAR as N83-18910
Accession ID: 84A16971
Document ID: 19840034184
No Digital Version Available - Go to Tips on Ordering
Updated/Added to NTRS: 2004-11-03

43.     Advanced rotary engines
Jones, C.
NASA Center for AeroSpace Information (CASI)
NASA. Lewis Research Center Aviation Gasolines and Future Alternatives, p 123-137 , 19830501; May 1, 1983
The broad objectives of this paper are the following: (1) to summarize the Curtiss-Wright design, development and field testing background in the area of rotary aircraft engines; (2) to briefly summarize past activity and update development work in the area of stratified charge rotary combustion engines; and (3) to discuss the development of a high-performance direct injected unthrottled stratified charge rotary combustion aircraft engine. Efficiency improvements through turbocharging are also discussed.
Accession ID: 83N22454
Document ID: 19830014183
No Digital Version Available - Order This Document from CASI
Updated/Added to NTRS: 2004-11-03

44.     Study of advanced rotary combustion engines for commuter aircraft
Berkowitz, M.; Jones, C.; Myers, D.
NASA Center for AeroSpace Information (CASI)
NASA-CR-165399; NAS 1.26:165399; CW-WR-81-022F , 19830201; Feb 1, 1983
Performance, weight, size, and maintenance data for advanced rotary aircraft engines suitable for comparative commuter aircraft system evaluation studies of alternate engine candidates are provided. These are turbocharged, turbocompounded, direct injected, stratified charge rotary engines. Hypothetical engines were defined (an RC4-74 at 895 kW and an RC6-87 at 1490 kW) based on the technologies and design approaches used in the highly advanced engine of a study of advanced general aviation rotary engines. The data covers the size range of shaft power from 597 kW (800 hp) to 1865 kW (2500 hp) and is in the form of drawings, tables, curves and written text. These include data on internal geometry and configuration, installation information, turbocharging and turbocompounding arrangements, design features and technologies, engine cooling, fuels, scaling for weight size BSFC and heat rejection for varying horsepower, engine operating and performance data, and TBO and maintenance requirements. The basic combustion system was developed and demonstrated; however the projected power densities and performance efficiencies require increases in engine internal pressures, thermal loading, and rotative speed.
Accession ID: 83N17545
Document ID: 19830009274
No Digital Version Available - Order This Document from CASI
Updated/Added to NTRS: 2004-11-03

45.     Multi-fuel rotary engine for general aviation aircraft
Jones, C.; Ellis, D. R.; Meng, P. R.
NASA Center for AeroSpace Information (CASI)
NASA-TM-83429; E-1718; NAS 1.15:83429; AIAA PAPER 83-1340; Joint Propulsion Conf., Seattle, 27-29 Jun. 1983 , 19830101; JAN 1, 1983
Design studies of advanced multifuel general aviation and commuter aircraft rotary stratified charge engines are summarized. Conceptual design studies were performed at two levels of technology, on advanced general aviation engines sized to provide 186/250 shaft kW/hp under cruise conditions at 7620 (25000 m/ft) altitude. A follow on study extended the results to larger (2500 hp max.) engine sizes suitable for applications such as commuter transports and helicopters. The study engine designs were derived from relevant engine development background including both prior and recent engine test results using direct injected unthrottled rotary engine technology. Aircraft studies, using these resultant growth engines, define anticipated system effects of the performance and power density improvements for both single engine and twin engine airplanes. The calculated results indicate superior system performance and 27 to 33 percent fuel economy improvement for the rotary engine airplanes as compared to equivalent airframe concept designs with current baseline engines. The research and technology activities required to attain the projected engine performance levels are also discussed.
Accession ID: 83N29235
Document ID: 19830020964
No Digital Version Available - Order This Document from CASI
Updated/Added to NTRS: 2004-11-03

47.     Advanced general aviation engine/airframe integration study
Zmroczek, L. A.
NASA Center for AeroSpace Information (CASI)
NASA-CR-165565; NAS 1.26:165565 , 19820301; Mar 1, 1982
A comparison of the in-airframe performance and efficiency of the advanced engine concepts is presented. The results indicate that the proposed advanced engines can significantly improve the performance and economy of general aviation airplanes. The engine found to be most promising is the highly advanced version of a rotary combustion (Wankel) engine. The low weight and fuel consumption of this engine, as well as its small size, make it suited for aircraft use.
Accession ID: 82N22268
Document ID: 19820014394
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Updated/Added to NTRS: 2005-08-25

48.     Advanced stratified charge rotary aircraft engine design study
Badgley, P.; Berkowitz, M.; Jones, C.; Myers, D.; Norwood, E.; Pratt, W. B.; Ellis, D. R.; Huggins, G.; Mueller, A.; Hembrey, J. H.
NASA Center for AeroSpace Information (CASI)
NASA-CR-165398; NAS 1.26:165398; CW-WR-81.021 , 19820129; Jan 29, 1982
A technology base of new developments which offered potential benefits to a general aviation engine was compiled and ranked. Using design approaches selected from the ranked list, conceptual design studies were performed of an advanced and a highly advanced engine sized to provide 186/250 shaft Kw/HP under cruise conditions at 7620/25,000 m/ft altitude. These are turbocharged, direct-injected stratified charge engines intended for commercial introduction in the early 1990's. The engine descriptive data includes tables, curves, and drawings depicting configuration, performance, weights and sizes, heat rejection, ignition and fuel injection system descriptions, maintenance requirements, and scaling data for varying power. An engine-airframe integration study of the resulting engines in advanced airframes was performed on a comparative basis with current production type engines. The results show airplane performance, costs, noise & installation factors. The rotary-engined airplanes display substantial improvements over the baseline, including 30 to 35% lower fuel usage.
Accession ID: 82N27743
Document ID: 19820019867
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Updated/Added to NTRS: 2005-08-25

50.     Assessment of advanced technologies for high performance single-engine business airplanes
Kohlman, D. L.; Holmes, B. J.
NASA Center for AeroSpace Information (CASI)
International Council of the Aeronautical Sciences, Seattle, WA, August 22-27, 1982 , 19820101; JAN 1, 1982
The prospects for significantly increasing the fuel efficiency and mission capability of single engine business aircraft through the incorporation of advanced propulsion, aerodynamics and materials technologies are explored. It is found that turbine engines cannot match the fuel economy of the heavier rotary, diesel and advanced spark reciprocating engines. The rotary engine yields the lightest and smallest aircraft for a given mission requirement, and also offers greater simplicity and a multifuel capability. Great promise is also seen in the use of composite material primary structures in conjunction with laminar flow wing surfaces, a pusher propeller and conventional wing-tail configuration. This study was conducted with the General Aviation Synthesis Program, which can furnish the most accurate mission performance calculations yet obtained.
Accession ID: 82A40932
Document ID: 19820057397
No Digital Version Available - Go to Tips on Ordering
Updated/Added to NTRS: 2004-11-03

59.     Multifuel rotary aircraft engine
Jones, C.; Berkowitz, M.
NASA Center for AeroSpace Information (CASI)
AIAA PAPER 80-1237; Joint Propulsion Conference, Hartford, CT, June 30-July 2, 1980 , 19800601; Jun 1, 1980
The broad objectives of this paper are the following: (1) to summarize the Curtiss-Wright design, development and field testing background in the area of rotary aircraft engines; (2) to briefly summarize past activity and update development work in the area of stratified charge rotary combustion engines; and (3) to discuss the development of a high-performance direct injected unthrottled stratified charge rotary combustion aircraft engine. Efficiency improvements through turbocharging are also discussed.
Accession ID: 80A38982
Document ID: 19800054812
No Digital Version Available - Go to Tips on Ordering
Updated/Added to NTRS: 2004-11-03


68.     A review of Curtiss-Wright rotary engine developments with respect to general aviation potential
Jones, C.
NASA Center for AeroSpace Information (CASI)
SAE PAPER 790621; Society of Automotive Engineers, Business Aircraft Meeting and Exposition, Wichita, KS, Apr. 3-6, 1979 , 19790401; Apr 1, 1979
Aviation related rotary (Wankel-type) engine tests, possible growth directions and relevant developments at Curtiss-Wright have been reviewed. Automotive rotary engines including stratified charge are described and flight test results of rotary aircraft engines are presented. The current 300 HP engine prototype shows basic durability and competitive performance potential. Recent parallel developments have separately confirmed the geometric advantages of the rotary engine for direct injected unthrottled stratified charge. Specific fuel consumption equal to or better than pre- or swirl-chamber diesels, low emission and multi-fuel capability have been shown by rig tests of similar rotary engine.
Accession ID: 79A36749
Document ID: 19790052736
No Digital Version Available - Go to Tips on Ordering
Updated/Added to NTRS: 2004-11-03

75.     Development status of rotary engine at Toyo Kogyo; for general aviation aircraft
Yamamoto, K.
NASA Center for AeroSpace Information (CASI)
NASA. Lewis Res. Center The Rotary Combust. Engine, p 37-84 , 19780101; JAN 1, 1978
Progress in the development of rotary engines which use a thermal reactor as the primary part of the exhaust emission control system is reviewed. Possibilities of further improvements in fuel economy of future rotary engines are indicated.
Accession ID: 79N15964
Document ID: 19790007793
No Digital Version Available - Order This Document from CASI
Updated/Added to NTRS: 2004-11-03

83.     Preliminary evaluation of a turbine/rotary combustion compound engine for a subsonic transport; fuel consumption and engine tests of turbofan engines
Civinskas, K. C.; Kraft, G. A.
NASA Center for AeroSpace Information (CASI)
NASA-TM-X-71906; E-8695 , 19760301; Mar 1, 1976
The fuel consumption of a modern compound engine with that of an advanced high pressure ratio turbofan was compared. The compound engine was derived from a turbofan engine by replacing the combustor with a rotary combustion (RC) engine. A number of boost pressure ratios and compression ratios were examined. Cooling of the RC engine was accomplished by heat exchanging to the fan duct. Performance was estimated with an Otto-cycle for two levels of energy lost to cooling. The effects of added complexity on cost and maintainability were not examined and the comparison was solely in terms of cruise performance and weight. Assuming a 25 percent Otto-cycle cooling loss (representative of current experience), the best compound engine gave a 1.2 percent improvement in cruise. Engine weight increased by 23 percent. For a 10 percent Otto-cycle cooling loss (representing advanced insulation/high temperature materials technology), a compound engine with a boost PR of 10 and a compression ratio of 10 gave an 8.1 percent lower cruise than the reference turbofan.
Accession ID: 76N21200
Document ID: 19760014112
No Digital Version Available - Order This Document from CASI
Updated/Added to NTRS: 2004-11-03


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