Improved gas turbine engine cycle including a heat exchanger

Improved gas turbine engine cycle including a heat exchanger

A heat exchanger 20 is arranged to receive both the by-pass flow 14 and the exhaust 16 from the low pressure core turbine 10 in heat exchange relationship to heat the by-pass flow which is then passed through a low pressure power turbine 22 on shaft 26. Shaft 26 may be so arranged to drive an aircra...

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1. Verfasser: RALPH MURCH DENNING
Format: Patent
Sprache:eng
Schlagworte:
BLASTING
COMBUSTION ENGINES
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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creator RALPH MURCH DENNING
description A heat exchanger 20 is arranged to receive both the by-pass flow 14 and the exhaust 16 from the low pressure core turbine 10 in heat exchange relationship to heat the by-pass flow which is then passed through a low pressure power turbine 22 on shaft 26. Shaft 26 may be so arranged to drive an aircraft propeller (or other load) through gearing 28. The exhausts of the two low pressure turbines 10, 22 pass to atmosphere through separate final nozzles 18 and 24.
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Shaft 26 may be so arranged to drive an aircraft propeller (or other load) through gearing 28. 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subjects BLASTING
COMBUSTION ENGINES
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
title Improved gas turbine engine cycle including a heat exchanger
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