Combustor skin assembly for gas turbine engine
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F23R-003/06
F23R-003/00
F23R-003/60
출원번호
US-0651527
(2012-10-15)
등록번호
US-9657949
(2017-05-23)
발명자
/ 주소
Stastny, Honza
Sze, Robert
출원인 / 주소
PRATT & WHITNEY CANADA CORP.
대리인 / 주소
Norton Rose Fulbright Canada LLP
인용정보
피인용 횟수 :
0인용 특허 :
11
초록▼
A combustor assembly includes a hot skin of a combustion chamber wall having an inner face exposed to the combustion chamber and an opposite outer face, a receiving skin having a securing portion affixed to the hot skin outer face in an air-tight manner and a receiving flange, extending from the sec
A combustor assembly includes a hot skin of a combustion chamber wall having an inner face exposed to the combustion chamber and an opposite outer face, a receiving skin having a securing portion affixed to the hot skin outer face in an air-tight manner and a receiving flange, extending from the securing portion, that is offset from the hot skin outer face to form a female recess, a cold skin having a cold wall portion spaced from the hot skin and forming a cooling cavity therebetween, a securing portion extending from a first end of the cold wall portion affixed to the hot skin outer face in an air-tight manner and a male flange extending from a second end of the cold wall portion opposite the first end, the male flange snugly received in the female recess and forming a sliding engagement therebetween.
대표청구항▼
1. A combustor skin assembly for a gas turbine engine, the combustor skin assembly comprising: a hot skin forming at least a portion of a wall of a combustion chamber of the gas turbine engine, the hot skin having an inner face exposed to the combustion chamber, and an outer face opposite the inner
1. A combustor skin assembly for a gas turbine engine, the combustor skin assembly comprising: a hot skin forming at least a portion of a wall of a combustion chamber of the gas turbine engine, the hot skin having an inner face exposed to the combustion chamber, and an outer face opposite the inner face;a receiving skin formed of sheet metal separate from the hot skin and having a securing portion affixed to the outer face of the hot skin in an air-tight manner, and a receiving flange extending from the securing portion, the receiving flange being offset an offset distance away from the outer face of the hot skin to form a female recess between the outer face of the hot skin and the receiving flange; anda cold skin formed of sheet metal separate from both the hot skin and the receiving skin and having a cold wall portion spaced from the hot skin and forming a cooling cavity therebetween, a securing portion extending from a first end of the cold wall portion and affixed to the outer face of the hot skin in an air-tight manner, and a male flange extending from a second end of the cold wall portion opposite the first end, the male flange having a thickness being greater than the offset distance of the female recess to be snugly received in the female recess and form a sliding engagement between the male flange and the female recess, the receiving flange and the hot skin applying a compressive force to the male flange therebetween during operation of the gas turbine engine. 2. The combustor skin assembly of claim 1 wherein the male flange is interference fit with the female recess at ambient temperatures. 3. The combustor skin assembly of claim 1 wherein the cold skin has a plurality of interspaced impingement holes, the hot skin has a plurality of interspaced effusion holes, and both the cold skin, the hot skin, and the receiving skin are provided in the form of annular components. 4. The combustor skin assembly of claim 1 wherein the hot skin, the cold skin, and the receiving skin are each made of sheet metal of a nickel-chromium based super alloy. 5. The combustor skin assembly of claim 1 wherein the female recess is enclosed by the receiving flange, the hot skin, and the securing portion of the receiving skin. 6. The combustor skin assembly of claim 1 wherein the securing portion of the cold skin is affixed to the hot skin by one of welding and brazing, and the securing portion of the receiving skin is affixed to the hot skin by welding. 7. A gas turbine engine having a combustor skin assembly comprising: a hot skin forming at least a portion of a wall of a combustion chamber of the gas turbine engine, the hot skin having an inner face exposed to the combustion chamber, and an outer face opposite to the inner face;a receiving skin formed of sheet metal separate from the hot skin and having a securing portion affixed to the outer face of the hot skin in an air-tight manner, and a receiving flange extending from the securing portion, the receiving flange being offset an offset distance from the outer face of the hot skin and forming a female recess; anda cold skin formed of sheet metal separate from both the hot skin and the receiving skin and having a cold wall portion spaced from the hot skin and forming a cooling cavity therebetween, a securing portion extending from a first end of the cold wall portion, affixed to the outer face of the hot skin in an air-tight manner, and a male flange extending from a second end of the cold wall portion opposite the first end, the male flange having a thickness being greater than the offset distance of the female recess to be snugly received in the female recess and form a sliding engagement therewith, the receiving flange and the hot skin applying a compressive force to the male flange therebetween during operation of the gas turbine engine. 8. The gas turbine engine having the combustor skin assembly of claim 7 wherein the cold skin has a plurality of interspaced impingement holes, the hot skin has a plurality of interspaced effusion holes, and both the cold skin, the hot skin, and the receiving skin are provided in the form of annular components. 9. The gas turbine engine having the combustor skin assembly of claim 7 wherein the hot skin, the cold skin, and the receiving skin are each made of sheet metal of a nickel-chromium based super alloy. 10. The gas turbine engine having the combustor skin assembly of claim 7 wherein the female recess is enclosed by the receiving flange, the hot skin, and the securing portion of the receiving skin. 11. The gas turbine engine having the combustor skin assembly of claim 7 wherein the corresponding securing portions of both the receiving skin and the cold skin are affixed to the hot skin by welding. 12. A method of assembling a combustor skin assembly comprising a hot skin forming at least a portion of a wall of a combustion chamber of a gas turbine engine, the hot skin having an inner face exposed to the combustion chamber, and an opposite outer face; a cold skin formed of sheet metal and having a securing portion extending from a first end, and a male flange extending from a second end opposite the first end, and a receiving skin separate from the hot skin and the cold skin formed of sheet metal and having a securing portion and a receiving flange extending from the securing portion, the method comprising affixing the securing portion of the cold skin to the hot skin in an air-tight manner, with a cold wall portion of the cold skin being spaced from the hot skin;positioning the receiving flange over the male flange, the male flange having a thickness being greater than a distance between the receiving flange and the outer surface of the hot skin; andaffixing the securing portion of the receiving skin to the hot skin, the male flange thereafter remaining compressively squeezed between the receiving flange and the hot skin.
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이 특허에 인용된 특허 (11)
Sterman Albert P. (Cincinnati OH) Wakeman Thomas G. (Cincinnati OH) Williams Jesse J. (Cincinnati OH), Combustion chamber construction.
McCaldon Kian,CAX ; Aze Robert Ming Lap,CAX ; Sampath Parthasarathy,CAX, Double pass air impingement and air film cooling for gas turbine combustor walls.
Ambrogi Christine J. M. (Bondoufle FRX) Ansart Denis R. H. (Bois Le Roi FRX) Meunier Serge M. (Le Chatelet En Brie FRX) Sandelis Denis J. M. (Nangis FRX), Double wall construction for a gas turbine combustion chamber.
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