Design and Test of a Small Turbine at 2500F with Transpiration Cooled Blading 690035
With the increasing need for high performance, small gas turbine engines in the 500–1000 hp
class, there is a requirement for use of high turbine inlet temperature in the range of 2500 F.
Engines designed at these temperatures will supply more than twice the horsepower available in
present day noncooled engines. Reliable operation of the turbine component at gas temperatures
that exceed the melting temperature of the materials, however, requires selection and
application of an efficient and practical blade cooling method. This paper presents the design
of a transpiration air cooled, single stage, high work, axial flow, small turbine suitable for
2500 F turbine inlet temperature and capable of driving an 8:1 pressure ratio 4 lb/sec
compressor. The manufacturing techniques associated with incorporating transpiration cooling
into the small blading and the electron beam welding of these blades to the disc to form an
integrally welded rotor assembly are also discussed. The results of the experimental testing of
cascade and full stage component of this small turbine design at gas temperatures to 2500 F are
presented.
Citation: Moskowitz, S. and Schober, T., "Design and Test of a Small Turbine at 2500F with Transpiration Cooled Blading ," SAE Technical Paper 690035, 1969, https://doi.org/10.4271/690035. Download Citation
Author(s):
S. L. Moskowitz, T. E. Schober
Affiliated:
Curtiss-Wright Corp
Pages: 13
Event:
1969 International Automotive Engineering Congress and Exposition
ISSN:
0148-7191
e-ISSN:
2688-3627
Related Topics:
Assembling
Welding
Compressors
Propellers and rotors
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