T63 REGENERATIVE ENGINE PROGRAM
Abstract
Application of regeneration to the small gas turbine engine can provide a significant improvement in Army aircraft range capability and in fuel logistics. However, very little is known about regenerator performance when tested under actual operating conditions. This is especially true of regenerative engine-aircraft compatibility. The program was oriented toward gaining this experience. The program was divided into three phases. Phase I consisted of the design and fabrication of the regenerator and required engine modifications. Phase II encompassed the engine testing required to ensure the flightworthiness of the regenerative engine. Phase III included modifications of a YOH-6A helicopter and flight test of the regenerative engine powered aircraft throughout its operating range. The test program demonstrated the feasibility of a regenerative engine as a powerplant for aircraft operation. A horsepower-to-weight ratio of 1.62 and a maximum specific range of 1.25 miles per pound of fuel were demonstrated. The addition of a regenerator increased the specific range of the YOH-6A aircraft by 25.7%. The performance at altitude agreed with the originally predicted values obtained by means of a computer program. The transient response of the regenerative engine powered aircraft was similar to that obtained using the prototype T63-A-5 nonregenerative engine.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1968
- Accession Number
- AD0675444
Entities
People
- Edward J. Privoznik
Organizations
- General Motors