| 摘要 |
A gas turbine engine 20 comprising a variable geometry engine compressor 24, a variable geometry engine turbine 30 coupled to the engine compressor and a combustor 28. The combustor has an inlet (34 figure 3) arranged to receive air from a first engine compressor outlet, and an outlet arranged to deliver combustion products to the engine turbine 30. A combustor bypass passage (50 figure 3) has an inlet (53 figure 3) arranged to receive air from a second engine compressor outlet and an outlet in fluid communication with a main fluid flow path downstream of a combustion zone (46, 48 figure 3) of the combustor, and upstream of a turbine inlet 31. Wherein, the combustor bypass passage comprises a bypass control valve 52 configured to selectively modulate the ratio of air flowing to the combustor inlet to air flowing through the bypass passage. |
