This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Small Turbine Advanced Gas Generator for Future Propulsion Requirements
Annotation ability available
Sector:
Language:
English
Abstract
On Nov. 30, 1971, the Eustis Directorate of the U.S. Army Air Mobility Research and Development Laboratory issued four contracts for the design, fabrication, and testing of the Small Turbine Advanced Gas Generator (STAGG). The STAGG airflow range is approximately 1-5 lb/s. The purpose of the STAGG program is to provide the core gas generator technology base for future small gas turbine engine programs for the Department of Defense (DOD) as well as the Army. The STAGG program will incorporate advanced component technology into a gas generator in order to define matching and integration problems at an early date, thereby reducing gas turbine engine development time and cost.
STAGG is a core gas generator (gas producer) with the compressor, combustor, turbine, and bearings and seals as prime interest areas. It includes laboratory (slave) inlet, exhaust nozzle, lubrication system, and fuel control system necessary for operation and testing. Two contracts are in the 1-2 and two contracts are in the 3-5 lb/s airflow size. The gas generators will not include accessory drive or power turbine systems.
Authors
Topic
Citation
Johnson, E. and Pedersen, M., "Small Turbine Advanced Gas Generator for Future Propulsion Requirements," SAE Technical Paper 720831, 1972, https://doi.org/10.4271/720831.Also In
References
- Bell L. E. “Design Requirements of Small High-Temperature-Rise Combustors.” SAE Transactions 77 1968 paper 680447
- Kailos N. C. “Increased Helicopter Capability Through Advanced Powerplant Technology.” 23rd National Forum American Helicopter Society
- Chauvin J. Papiliou K. Burrows L. T. “Aerodynamic Problems in Cooled Turbine Blade Design for a Small Gas Turbine.” 32nd AGARD PEP Sept. 9-13 1968
- Gabel R. M. Tabbey A. J. “Advancement of High-Temperature Turbine Technology for Small Gas Turbine Engines-Fluid-Cooled Axial Flow Turbine.” USAAVLABS Technical Report 68-65 January 1969
- Muller C. H. Cox L. R. “Single-Stage Axial Compressor Component Development for Small Gas Turbine Engines.” USAAVLABS Technical Report 68-90 1-3 June 1969
- Brown L. E. “Small Axial-Centrifugal Compressor Matching Study.” USAAVLABS Technical Report 70-20 May 1970
- Pampreen R. C. Firman P. A. Erwin J. R. Dawson R. W. “A Small Axial-Centrifugal Compressor Matching Study Program.” USAAVLABS Technical Report 70-34 October 1970
- Calvert G. S. Okapun U. “Design and Evaluation of a High Temperature Radial Turbine.” USAAVLABS Technical Reports 68-69 I II January 1969 May 1971
- Paladini W. “Static and Rotating Air/Gas Seal Evaluation.” USAAVLABS Technical Report 71-28 June 1971
- Johansen K. M. Duncan W. H. “Reverse-Flow Turboshaft Engine Study.” USAAVLABS Technical Report 70-48 October 1970
- Davis J. V. “Advancement of Small Gas Turbine Component Technology, Advanced Small Axial Compressor.” USAAV-LABS Technical Reports 69-10A and 69-10B December 1969 February 1970
- Welliver A. D. Acurio J. “Small Gas Turbine Component Technology-Compressor Research.” USAAVLABS Technical Reports 67-30 and 67-47 August September 1967
- Cale D. B. “Turbine Engine and Component Cost.” USAAVLABS Technical Report 68-59 July 1968
- Dean, R. C. Jr. Wright D. D. Runstadler, P. W. Jr. “Fluid Mechanics Analysis of High-Pressure Ratio Centrifugal Compressor Data.” USAAVLABS Technical Report 69-76 February 1970
- USA Aviation Material Laboratories Industrial Briefing Williamsburg, Va. Sept. 8-9 1969