| 摘要 |
A gas turbine engine including in-line intercooling wherein compressor intercooling is achieved without removing the compressor main flow airstream from the compressor flowpath is described. In an exemplary embodiment, a gas turbine engine suitable for use in connection with in-line intercooling includes a low pressure compressor, a high pressure compressor, and a combustor. The engine also includes a high pressure turbine, a low pressure turbine, and a power turbine. For intercooling, fins are located in an exterior surface of the compressor struts in the compressor flowpath between the outlet of the low pressure compressor and the inlet of the high pressure compressor. Coolant flowpaths are provided in the compressor struts, and such flowpaths are in flow communication with a heat exchanger. In operation, air flows through the low pressure compressor, and compressed air is supplied from the low pressure compressor to the high pressure compressor. The fins increase the heat transfer area between the gas turbine main compressor airflow and the coolant flow in the struts. Specifically, the flowpaths in the struts serve as heat sinks for cooling the high temperature compressor mainstream flow. The cooled airflow is supplied to the inlet of the high pressure compressor, and the highly compressed air is delivered to the combustor. Airflow from the combustor drives the high pressure turbine, the low pressure turbine, and the power turbine. Waste heat is captured by the boilers, and the heat from the boilers in the form of steam is delivered to upstream components. The steam could, alternatively, be delivered to a steam turbine or to other equipment.
|
