NASA Glenn · Guide to Aeronautics
NASA Glenn · Retrieved 2026-09-05
Educational reference; original Owl summariesPROPULSION
Gas-turbine thermodynamics
FLIGHT SCIENCE / CONCEPT REFERENCE
SCIENCEConditions & principles
The ideal Brayton cycle models compression, heat addition and expansion in a gas turbine.
REFERENCE COVERAGE3 / 3 editorial sections
PROVENANCE1 linked source
LAST RETRIEVED2026-09-05
Editorial section coverage describes the article structure, not scientific validation or completeness.
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Source editions
NASA Glenn · Guide to Aeronautics ↗Edition / snapshot: Reference snapshot, September 2026Retrieved: 2026-09-05
Retrieval dates record when Owl obtained the data; they are not publication dates or proof that a specification is current. Where the edition contains only a snapshot date, the original publication date is not recorded.
01
Mechanism
A compressor raises pressure, combustion adds heat and a turbine extracts work. In a jet engine, remaining energy accelerates the exhaust; a shaft engine extracts more as shaft power.
02
Aircraft response
Pressure ratio, temperature limits and component efficiency affect useful output and fuel demand. Real engines include losses and operating constraints.
03
Context & interpretation
The ideal cycle omits pressure losses, cooling flows and variable gas properties. It is a framework for understanding rather than a detailed engine model.
Physical relationship
ηideal = 1 − 1 / rp^((γ−1)/γ)Ideal thermal efficiency with constant gas properties; rp: compressor pressure ratio.
Sources & context
Educational explanation of physical mechanisms. Aircraft-specific procedures, limitations and current weather information are separate references.