To provide a method and device for operating a gas turbine engine in particular, in relation to a rotating machine.
A combustor assembly 104 includes at least one combustor wall 105 defining a combustion chamber 106, and at least one first fluid passage defining at least one first fluid inlet within the at least one combustor wall to inject a first fluid stream 132 into the combustion chamber. The first fluid passage is coupled in flow communication with the combustion chamber. The assembly further includes at least one second fluid passage 120 defining at least one second fluid inlet 126 within the at least one combustor wall. The at least one second fluid inlet 126 is positioned adjoining the at least one first fluid inlet and coupled in flow communication with the combustion chamber. The second fluid inlet is configured to inject a second fluid stream 130 into the combustion chamber at an oblique angle 134 with respect to the first fluid stream so that the first and second fluid streams intersect at a preset incident angle.
LACY BENJAMIN
LIPINSKI JOHN JOSEPH
| JPH05332540A | 1993-12-14 | |||
| JP2005326143A | 2005-11-24 | |||
| JP2004101175A | 2004-04-02 |
| US3603092A | 1971-09-07 | |||
| US4801092A | 1989-01-31 | |||
| US5437158A | 1995-08-01 |
Hirokazu Ogura
Toshihisa Kurokawa
Arakawa Satoshi