A gas turbine engine having a heat absorption device and an associated method are disclosed. The gas turbine engine includes a compressor having a compressor discharge nozzle, a combustor coupled to the compressor, a turbine coupled to the combustor and the compressor, a fluid flow passage fluidly coupling the compressor and the turbine and bypassing the combustor, and a heat absorption device disposed fluidly along the fluid flow passage at a first predefined location. The heat absorption device includes a casing having an inlet and an outlet, a flow path within the casing and extending between the inlet and the outlet, wherein the flow path directs an input bleed flow diverted from a fluid stream discharged from the compressor, and a phase change material hermetically sealed within the casing. The phase change material is separated from the flow path. The heat absorption device is configured to exchange heat between the phase change material and the input bleed flow to generate an output bleed flow of a different temperature than the input bleed flow and discharge the output bleed flow to a second predefined location different from the first predefined location.
Gas turbine engine having a heat absorption device and an associated method thereof
2021-12-07
Patent
Electronic Resource
English
IPC: | F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F28D Wärmetauscher, soweit in keiner anderen Unterklasse vorgesehen, in denen die Wärmetauschmittel nicht in direkte Berührung miteinander kommen , HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT |
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