The research and development of a unique combustion engine is presented. The engine converts the thrust from ramjet modules located on the rim of a disk into shaft torque, which in turn can be used for electrical power generation or mechanical drive applications. A test program was undertaken that included evaluation of the pre-prototype engine and incorporation of improvements to the thrust modules and supporting systems. Fuel mixing studies with vortex generators and bluff-body flame holders demonstrated the importance of increasing the shear-layer area and spreading angle to augment flame volume. Evaluation of flame-holding configurations (with variable fuel injection methods) concluded that the heat release zone, and therefore combustion efficiency, could be manipulated by judicious selection of bluff-body geometry, and is less influenced by fuel injection distribution. Finally, successful operation of novel fuel and cooling air delivery systems have resolved issues of gas (fuel and air) delivery to the individual rotor segments. The lessons learned from the pre-prototype engine are currently being applied to the development of a 2.8MW engine.

Issue Section:
Gas Turbines: Combustion and Fuels
Keywords:
gas turbines, gas turbine power stations, internal combustion engines, fuel, combustion, flames
Topics:
Combustion, Engines, Flames, Fuels, Combustion chambers, Temperature, Ramjets, Rotors, Engineering prototypes
1.
Heiser, W. H., and Pratt, D. T., 1994, Hypersonic Airbreathing Propulsion (AIAA Ed. Series), AIAA, Washington, DC.
2.
Oates, G. C., 1997, Aerothermodynamics of Gas Turbine and Rocket Propulsion (AIAA Ed. Series) AIAA, Washington, DC.
3.
Bogdanoff
,
D. W.
,
1992
, “
Ram Accelerator Direct Space Launch System: New Concepts
,”
J. Propul. Power
,
8
(
2
), pp.
481
–
490
.
4.
Harsha
,
P. T.
, and
Edelman
,
R. B.
,
1981
, “
Assessment of a Modular Ramjet Combustion Model
,”
J. Spacecraft
,
19
(
3
), pp.
430
–
436
.
5.
Hertzberg
,
A.
,
Bruckner
,
A. P.
, and
Bogdanoff
,
D. W.
,
1988
, “
Ram Accelerator: A New Chemical Method for Accelerating Projectiles to Ultrahigh Velocities
,”
AIAA J.
,
26
(
2
), pp.
195
–
203
.
6.
Yungster
,
S.
,
Eberhardt
,
S.
, and
Bruckner
,
A. P.
,
1991
, “
Numerical Simulation of Hypervelocity Projectiles in Detonable Gases
,”
AIAA J.
,
29
(
2
), pp.
187
–
193
.
7.
Kendrick
,
D. W.
,
Anderson
,
T. J.
,
Sowa
,
W. A.
, and
Snyder
,
T. S.
,
1999
, “
Acoustic Sensitivities of Lean-Premixed Fuel Injectors in a Single Nozzle Rig
,”
ASME J. Eng. Gas Turbines Power
,
121
, pp.
429
–
436
.
8.
Snyder, T. S., Rosfjord, T. J., McVey, J., Hu, A., and Schlein, B., 1994, “Emissions and Performance of a Lean-Premixed GasFuel Injection System for Aeroderivative Gas Turbine Engines,” ASME Paper No. 94-GT-234.
9.
Eckbreth, A. C., 1988, Laser Diagnostics for Combustion Temperature and Species, Turnbridge Wells, Kent, UK.
10.
Kreith, F., and Bohn, M. S., 1986, The Principals of Heat Transfer, Harper and Row, Cambridge, UK.
11.
Schlichting, H., 1979, Boundary-Layer Theory, McGraw-Hill, New York.
12.
Ozawa, R. I., 1981, “Survey of Basic Data on Flame Stabilization and Propagation for High Speed Combustion Systems,” Paper No. AFAPL-TR70-81.
13.
Zukoski, E. E., 1978, “Afterburners,” The Aerothermodynamics of Aircraft Gas Turbine Engines, Gordon C. Oates, ed., Air Force Propulsion Laboratory, AFAPL-TR-78-52, Chap. 21.
14.
Glassman, I., 1987, Combustion, Academic Press, San Diego, CA.
15.
Lefebvre, A. H., 1983, Gas Turbine Combustion, Hemisphere, Washington, DC.
Copyright © 2003
 by ASME
You do not currently have access to this content.