To improve combustion efficiency and profile/pattern factor of combustion.
This turbomachine (2) includes a compressor (4), a combustor (6) including a first end operatively connected to the compressor (4) and a second end, a transition piece (55) mounted to the second end of the combustor (6), and the injection device (90) mounted to one of the combustor (6) and the transition piece (55). The injection device (90) includes a first end portion (112), and a second end portion (114) which the first end portion (112) reaches through an intermediate portion (116). The intermediate portion (116) includes a flow conditioning mechanism (124). Combustion air from the compressor (4) enters the first end portion (112), passes through the flow conditioning mechanism (124), and enters into one of the combustion liner (6) and transition piece (55). The flow conditioning mechanism (124) creates an air flow disturbance in the combustion air to promote mixing of combustion gases.
| JPS57202431 | COMBUSTOR FOR GAS TURBINE |
| JPH0345816 | COOLING STRUCTURE FOR GAS TURBINE BURNER |
| JPS59112129 | LINER FOR BURNER |
| JPH02183721A | 1990-07-18 | |||
| JPH02187520A | 1990-07-23 | |||
| JPH07233945A | 1995-09-05 |
Hirokazu Ogura
Toshihisa Kurokawa
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