[특허]Turbine nozzle baffle

United Technologies Corporation

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특허 상세정보

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Turbine nozzle baffle

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-025/24 F01D-025/12 F01D-011/00
출원번호	US-0692171 (2012-12-03)
등록번호	US-9291071 (2016-03-22)
발명자 / 주소	Jewess, Gordon F.
출원인 / 주소	United Technologies Corporation
대리인 / 주소	Kinney & Lange, P.A.
인용정보	피인용 횟수 : 0 인용 특허 : 16

초록
▼

An embodiment of the present invention is a turbine nozzle baffle including an annular box structure. The turbine nozzle baffle includes a first diaphragm, a second diaphragm, and a static portion of a rotating seal that form a one-piece annular box structure. The first diaphragm extends from an inner diameter of the box structure to an outer diameter of the box structure to form a first axial side. The second diaphragm includes a first portion and a second portion. The first portion extends from the inner diameter to the outer diameter to form a second axial side. The second portion extends toward the first axial side to form the outer diameter. The second diaphragm connects to the first diaphragm at the outer diameter. The static portion of the rotating seal faces radially inward at the inner diameter between the first axial side and the second axial side.

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청구항
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1. A turbine nozzle baffle including an annular box structure, the baffle comprising: a first diaphragm extending from an inner diameter of the annular box structure to an outer diameter of the annular box structure to form a first axial side and including a flange projecting radially outward from the outer diameter of the annular box structure at the first axial side;a second diaphragm, a first portion of the second diaphragm extending from the inner diameter to the outer diameter to form a second axial side, the second axial side spaced apart from the first axial side in an axial direction; a second portion of the second diaphragm extending toward the first axial side to form the outer diameter of the annular box structure; the second diaphragm connected to the first diaphragm at the outer diameter;a static portion of a rotating seal facing radially inward at the inner diameter between the first axial side and the second axial side; andan interference fit ring connected to the outer diameter of the annular box structure at the second axial side;wherein the first diaphragm, the second diaphragm, and the static portion of the rotating seal are connected together to form the annular box structure. 2. The baffle of claim 1, wherein the interference fit ring is a cast ring including a machined outside diameter surface. 3. The baffle of claim 2, wherein the static portion of the rotating seal connects to each of the first diaphragm and the second diaphragm at the inner diameter. 4. The baffle of claim 3, wherein the connections between the first diaphragm, and the second diaphragm; the static portion of the rotating seal, and each of the first diaphragm and the second diaphragm; and the interference fit ring, and the second diaphragm are brazed connections. 5. The baffle of claim 4, wherein the first diaphragm and the second diaphragm are formed from sheet metal. 6. The baffle of claim 5, wherein at least one of the sheet metal and the interference fit ring is made of a nickel-based alloy. 7. The baffle of claim 1, further including a plurality of lightening holes through the box structure at the outer diameter. 8. An axial gas turbine engine comprising: a first turbine rotor;a second turbine rotor;a rotor shaft connecting the first turbine rotor to the second turbine rotor, the rotor shaft including a rotating portion of a rotating seal;a turbine nozzle between the first turbine rotor and the second turbine rotor;a turbine nozzle baffle connected to an inner diameter of the turbine nozzle, the turbine nozzle baffle including an annular box structure wherein the turbine nozzle baffle comprises:a first diaphragm extending from an inner diameter of the annular box structure to an outer diameter of the annular box structure to form a first axial side; and including an annular flange projecting radially outward from the outer diameter of the annular box structure at the first axial side;a second diaphragm, a first portion of the second diaphragm extending from the inner diameter of the annular box structure to the outer diameter of the annular box structure to form a second axial side, the second axial side spaced apart from the first axial side in an axial direction; a second portion of the second diaphragm extending toward the first axial side to form the outer diameter of the annular box structure; the second diaphragm connected to the first diaphragm at the outer diameter of the annular box structure;a static portion of a rotating seal facing radially inward at the inner diameter of the annular box structure between the first axial side and the second axial side; andan interference fit ring connected to the outer diameter of the baffle at the second axial side;wherein the first diaphragm, the second diaphragm, and the static portion of the rotating seal are connected together to form the annular box structure. 9. The engine of claim 8 wherein the static portion of the rotating seal and the rotating portion of the rotating seal cooperate to form a seal between a first cavity between the first turbine rotor and first axial side, and a second cavity between the second turbine rotor and the second axial side. 10. The engine of claim 8, wherein the first axial side is contoured to match a contour of the first turbine rotor and the second axial side is contoured to match a contour of the second turbine rotor. 11. The engine of claim 8, further including a retaining ring; wherein: the turbine nozzle includes: a flange recess extending circumferentially around the inner diameter of the turbine nozzle; anda retaining ring slot extending circumferentially around the inner diameter of the turbine nozzle adjacent to the flange slot; andthe flange is disposed within the flange recess, and the retaining ring is disposed within the retaining ring slot to retain the flange within the flange recess to connect the flange to the inner diameter of the turbine nozzle. 12. The engine of claim 8 , wherein the static portion of the rotating seal connects to each of the first diaphragm and the second diaphragm at the inner diameter of the baffle. 13. A method of installing a turbine nozzle baffle in an inner diameter of a turbine nozzle comprises: altering the temperature of at least one of the turbine nozzle baffle and the turbine nozzle such that an outer diameter of an interference fit ring connected to an outer diameter of the turbine nozzle baffle fits within an inner diameter of the turbine nozzle;inserting the turbine nozzle baffle into the inner diameter of the turbine nozzle until a flange of the turbine nozzle baffle contacts a flange recess in the inner diameter of the turbine nozzle;securing the flange against the flange recess; andallowing the temperature of the turbine nozzle baffle and the turbine nozzle to equilibrate. 14. The method of claim 13, wherein securing the flange against the flange recess includes: compressing a retaining ring;inserting the compressed retaining ring into the inner diameter of the turbine nozzle until it contacts the flange of the turbine nozzle baffle; andreleasing the compressed retaining ring such that it expands into a retaining ring slot in the inside diameter of the turbine nozzle, adjacent to the flange recess. 15. The method of claim 13, wherein securing the flange against the flange recess includes: aligning flange openings in the flange with recess openings at the flange recess;inserting fasteners into the aligned flange openings and recess openings; andsecuring the fasteners such that the flange is secured against the flange recess. 16. A turbine nozzle baffle, including an annular box structure, the baffle comprising: a first diaphragm extending from an inner diameter of the annular box structure to an outer diameter of the annular box structure to form a first axial side;a second diaphragm, a first portion of the second diaphragm extending from the inner diameter of the annular box structure to the outer diameter of the annular box structure to form a second axial side, the second axial side spaced apart from the first axial side in an axial direction; a second portion of the second diaphragm extending toward the first axial side to form the outer diameter of the annular box structure; the second diaphragm connected to the first diaphragm at the outer diameter of the annular box structure; anda static portion of a rotating seal facing radially inward at the inner diameter of the annular box structure between the first axial side and the second axial side;wherein the first diaphragm, the second diaphragm, and the static portion of the rotating seal are connected to form the annular box structure, andwherein the annular box structure includes a plurality of lightening holes through the outer diameter. 17. The baffle of claim 16, wherein the first diaphragm includes a flange projecting radially outward from the outer diameter at the first axial side. 18. The baffle of claim 17, further including an interference fit ring connected to the outer diameter at the second axial side, wherein the interference fit ring is a cast ring including a machined outside diameter surface. 19. The baffle of claim 18, wherein the static portion of the rotating seal connects to each of the first diaphragm and the second diaphragm at the inner diameter. 20. The baffle of claim 19, wherein the connections between the first diaphragm, and the second diaphragm; the static portion of the rotating seal, and each of the first diaphragm and the second diaphragm; and the interference fit ring, and the second diaphragm are brazed connections. 21. The baffle of claim 20, wherein the first diaphragm and the second diaphragm are formed from sheet metal. 22. The baffle of claim 21, wherein at least one of the sheet metal and the interference fit ring is made of a nickel based alloy. 23. An axial gas turbine engine comprising: a first turbine rotor; a second turbine rotor; a rotor shaft connecting the first turbine rotor to the second turbine rotor; a turbine nozzle between the first turbine rotor and the second turbine rotor wherein the turbine nozzle includes an outer shroud, an inner shroud, and vanes extending between the inner shroud and the outer shroud, wherein the inner shroud of the turbine nozzle, the first turbine rotor, and the second turbine rotor define a cavity located radially inward from the inner shroud and between the first turbine rotor and the second turbine rotor; and a turbine nozzle baffle connected to an inner wall of the inner shroud and located in the cavity between the first and second turbine rotors, wherein the turbine nozzle baffle includes an annular box structure having a first axial side contoured to match a contour of the first turbine rotor and having a second axial side contoured to match a contour of the second turbine rotor, wherein the annular box structure includes a plurality of lightening holes through an outer diameter of the annular box structure.

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Turbine nozzle baffle

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Turbine nozzle baffle

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이 특허에 인용된 특허 (16)

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