INTERMEDIATE COOLING DEVICE FOR GAS TURBINE AND GAS TURBINE USING SAME

WIPO Patent Application WO/2012/014401

A1

A gas turbine (1) comprises: multiple stage compressors (2, 3); a combustor (4) for injecting a fuel into air compressed by the compressors and combusting the fuel; and a turbine (5) driven by the combustion gas from the combustor. In the gas turbine, a heat exchanger (7) is installed between the compressor stages. The heat exchanger is used for heating the working gas of a Stirling engine (8) serving as an intermediate cooling device and is disposed in a flow path of compressed air compressed by the compressors to directly exchange heat between the compressed air and the working gas. This makes it possible to effectively use the waste heat of the gas turbine and to provide a relatively small-type and light weight intermediate cooling device, the leakage failure of which even does not pose a problem to the operation of the gas turbine. In the case of an aircraft gas turbine, a low-temperature-side heat exchanger (11) of the Stirling engine is disposed so that a low temperature atmosphere passes therethrough.

MIYAMAE RYO
OHNO TATSUYA
MAEDA KENICHI
TAKAHASHI SHOICHI

PCT/JP2011/004027

February 02, 2012

July 14, 2011

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KAWASAKI HEAVY IND LTD (JP)
MIYAMAE RYO
OHNO TATSUYA
MAEDA KENICHI
TAKAHASHI SHOICHI

F01K23/02; F02C3/22; F02C7/143; F02G1/055

JP2008208836A	2008-09-11
JPH04128541A	1992-04-30
JP2009057969A	2009-03-19
JP2008175151A	2008-07-31
JP2009144538A	2009-07-02
JPH01151724A	1989-06-14
JP2009057972A	2009-03-19

PATENT CORPORATE BODY ARCO PATENT OFFICE (JP)
Patent business corporation Owner old patent firm (JP)

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