GAS TURBINE

A gas turbine (10) comprises a compressor (12), an annular combustion chamber (13), and a turbine (15), a combustion chamber shell (20a) of the combustion chamber (13) adjoining the turbine inlet (26) in a transition region (A) in order to introduce the hot gases generated in the combustion chamber...

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Bibliographic Details
Main Authors NARANCIC SINISA, FILKORN GUENTER, TSCHUOR REMIGI
Format Patent
LanguageChinese
English
Published 24.12.2014
Subjects
BLASTING
COMBUSTION APPARATUS
COMBUSTION PROCESSES
GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
HEATING
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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Summary:A gas turbine (10) comprises a compressor (12), an annular combustion chamber (13), and a turbine (15), a combustion chamber shell (20a) of the combustion chamber (13) adjoining the turbine inlet (26) in a transition region (A) in order to introduce the hot gases generated in the combustion chamber (13) into the downstream turbine (15) such that a thermal expansion-induced relative movement between the combustion chamber (13) and the turbine inlet (26) is possible. Combustion chamber shell (20a) support elements (29) distributed on the periphery come into contact with a conical contour (31a) on the shaft cover (25) due to the thermal expansion (33) that occurs during operation and are supported on said contour. The aim of the invention is an improvement with respect to loading and service life. This is achieved in that the conical contour (31a) and the machine axis form an angle (alpha2) that allows the combustion chamber shell (20a) support elements (29) to slide onto the conical contour (31a).
Bibliography:Application Number: CN201280052419