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특허 상세정보

Cooled gas turbine engine component

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F01D-005/18    F01D-025/12   
출원번호 US-0141912 (2013-12-27)
등록번호 US-9874110 (2018-01-23)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Barnes & Thornburg LLP
인용정보 피인용 횟수 : 0  인용 특허 : 74

A gas turbine component having a cooling passage is disclosed. In one form, the passage is oriented as a turned passage capable of reversing direction of flow, such as a turned cooling hole. The gas turbine engine component can include a layered structure having cooling flow throughout a region of the component. The cooling hole can be in communication with a space in the layered structure. The gas turbine engine component can be a cast article where a mold can be constructed to produce the cooling hole having a turn.


1. An apparatus comprising: a cooled gas turbine engine component having a leading edge, a trailing edge spaced apart from the leading edge, and a midspan located between the leading edge and the trailing edge, the component including an inner wall that defines a plenum and an outer wall arranged around the inner wall;a first internal passage located between the inner wall and the outer wall and used for conveyance of a cooling fluid, the first internal passage fluidly connected to the plenum on a suction side of the component near the midspan;a first co...

이 특허에 인용된 특허 (74)

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