To provide a communicating structure of a combustor transition pipe and a turbine inlet capable of improving turbine efficiency, by optimizing the relative position relationship between the combustor transition pipe and a first stage stationary blade.
A gas turbine generates motive power, by successively passing combustion gas through a plurality of turbine stages composed of the stationary blade 7 and a moving blade 8 arranged in a plurality in the peripheral direction of a combustion gas passage part in the turbine, by making the combustion gas generated by combustion flow in a turbine 6 inlet from the respective combustor transition pipes, by burning fuel by compressed air from an air compressor 4 in combustors 1 arranged in a plurality around a rotary shaft. The combustor transition pipes are communicated with and connected to the turbine inlet so that a wake flow 12 formed between the adjacent combustor transition pipes 5 is made to flow in the pressure surface 7a side near the leading edge of the first stage stationary blade.
| JP2024067772 | cylindrical body |
| WO/2023/127727 | COMBUSTOR FOR GAS TURBINE |
| JP2017020421 | METHOD OF REPAIRING TURBINE COMPONENT, AND TURBINE COMPONENT |
Tadahiro Mitsuishi
Yasuyuki Tanaka
Hiroshi Matsumoto