| 摘要 |
This invention concerns a system for cooling components in a gas turbine engine, the gas turbine engine comprising a compressor for driving a primary gas flow to a combustor and a turbine arranged to be driven by combustion gases from the combustor, wherein the system comprises: an annular cooling flow passage arranged for fluid communication between the compressor and the turbine, the flow passage having a first inlet arranged to receive gas from the primary gas flow downstream of compressor, and a second inlet located upstream of the first inlet, wherein the annular cooling flow passage has at least one internal wall 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. |
