Compressor and Turbine Matching Considerations in Turboprop Engines

570013

01/01/1957

Event
Pre-1964 SAE Technical Papers
Authors Abstract
Content
MATCHING studies of three turboprop engine configurations were made for flight conditions from sea-level static to 600 mph at 40,000 ft.
It is concluded that turbine frontal area, stress, and pressure ratio requirements made exhaust-area adjustment desirable. Sfc depended primarily upon flight conditions and turbine temperature, with lowest sfc occurring at highest turbine temperature, flight velocity, and altitude.
Free turbines restricted turbine temperature range and produced critical turbine requirements. Increasing a two-spool engine's outer-compressor pressure ratio increased turbine temperature range and made turbine requirements less critical.
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DOI
https://doi.org/10.4271/570013
Pages
12
Citation
Davison, E., "Compressor and Turbine Matching Considerations in Turboprop Engines," SAE Technical Paper 570013, 1957, https://doi.org/10.4271/570013.
Additional Details
Publisher
Published
Jan 1, 1957
Product Code
570013
Content Type
Technical Paper
Language
English