| 摘要 |
<p>This invention concerns a system 100 for cooling components in a gas turbine engine (10, Fig 1), the gas turbine engine comprising a compressor 102 for driving a primary gas flow to a combustor 104 and a turbine 106 arranged to be driven by combustion gases from the combustor. The system comprises an annular cooling flow passage 108 arranged for fluid communication between the compressor and the turbine, the flow passage having a first inlet 118 arranged to receive gas from the primary gas flow A downstream of the compressor, and a second inlet 120 located upstream of the first inlet. The annular cooling flow passage has at least one internal wall 128 for guiding airflow from the first inlet towards the airflow from the second inlet, such that the airflow from the first and second inlets coalesce within the annular flow passage prior to passing along the flow passage in a direction from the compressor to the turbine. The internal wall may guide the airflow from the first inlet in a rearward direction from the turbine to the compressor.</p> |
