Study of a Lightweight Integral Regenerative Gas Turbine for High Performance
Abstract
Two integrated engine concepts were designed by utilizing an annular recuperator of tubular construction wrapped around the turbomachinery to give compact, lightweight engine packages. In both designs, the recuperator is considered to be prime structure and acts as the structural backbone of the engine assembly. For the cycle conditions, with an airflow of 5 lb/sec, pressure ratio of 9:1, and a turbine inlet temperature of 2300F, a family of lightweight engine designs was established over a range of recuperator effectiveness from 0. 40 to 0.80 and a range of pressure loss from 4 percent to 10 percent. At the extreme end of the ranges of variables, an engine design is included with a specific fuel consumption of 0.333 lb/hp hr, the corresponding specific power being 194.70 hp/lb/sec. This performance is achieved within an engine envelope of 23.18 in. diameter by 33.0 in. length; the specific weight of the unit is 49. 66 lb/lb/sec. In the analysis, a reference engine design was established with a recuperator effectiveness and pressure loss of 0.65 and 6 percent respectively. With an SFC and specific power of 0.365 and 192.54 respectively, the specific weight of the lightest design was 34.72. This performance is achieved within an engine envelope of 19.04 in. diameter by 28.5 in. length and at an estimated cost of $42.9/horsepower.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1970
- Accession Number
- AD0877464
Entities
People
- Colin F. Mcdonald