Gas turbine with gap sealing between gas-washed components
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02K-001/80
B29C-065/54
F02K-003/04
F01D-011/00
출원번호
US-0494197
(2014-09-23)
등록번호
US-10047698
(2018-08-14)
우선권정보
GB-1319256.2 (2013-10-31)
발명자
/ 주소
Hicklin, Mark
Smith, Darren Robert
출원인 / 주소
ROLLS-ROYCE plc
대리인 / 주소
Oliff PLC
인용정보
피인용 횟수 :
0인용 특허 :
4
초록▼
A gas turbine engine having a fan and a bypass duct for discharging airflow from the fan to generate engine thrust. The bypass duct includes a first component and a second component each having a gas washed surface, the first component being positioned adjacent the second component with a gap thereb
A gas turbine engine having a fan and a bypass duct for discharging airflow from the fan to generate engine thrust. The bypass duct includes a first component and a second component each having a gas washed surface, the first component being positioned adjacent the second component with a gap therebetween. A sealing strip is positioned in the gap between the first component and the second component distal to the gas washed surfaces of the first and second components. A sealant is positioned between the first and second component proximal to the gas washed surfaces of the first and second components, so as to seal the gap between the first component and the second component from airflow through the bypass duct.
대표청구항▼
1. A gas turbine engine having a fan and a bypass duct for discharging airflow from the fan to generate engine thrust, the bypass duct comprising: a first component and a second component each having a gas washed surface, the first component being positioned adjacent the second component with a gap
1. A gas turbine engine having a fan and a bypass duct for discharging airflow from the fan to generate engine thrust, the bypass duct comprising: a first component and a second component each having a gas washed surface, the first component being positioned adjacent the second component with a gap therebetween;a sealing strip made from a compressible material in the shape of a hollow tube, the sealing strip positioned in the gap between the first component and the second component distal to the gas washed surfaces of the first and second components; anda sealant positioned between the first and second component proximal to the gas washed surfaces of the first and second components, so as to seal the gap between the first component and the second component from airflow through the bypass duct,wherein the first or second component comprises a plurality of projections configured so as to compress the sealing strip in the gap and arranged so as to define a plurality of pockets in the sealing strip. 2. The gas turbine engine according to claim 1, wherein the first component comprises a lip to limit movement of the sealing strip and/or sealant relative to the first component. 3. The gas turbine engine according to claim 2, wherein the lip is positioned to contact the sealant and form part of the gas washed surface of the first component. 4. The gas turbine engine according to claim 1, wherein the sealing strip is made from a rubber, elastomer or compressible closed cell foam. 5. The gas turbine engine according to claim 1, wherein the sealing strip has cross section that is substantially rectangular with rounded ends or substantially circular. 6. The gas turbine engine according to claim 1, wherein the plurality of projections comprises one or more radially extending projections. 7. The gas turbine engine according to claim 1, wherein opposing faces of the first component and the second component comprise a groove, and wherein the sealing strip extends into the groove of the first and second components. 8. The gas turbine engine according to claim 7, wherein the sealing strip has two bulbous ends, the bulbous ends being positioned in the grooves of the first and second components. 9. The gas turbine engine according to claim 1, wherein the first and/or second component is a liner or infill. 10. The gas turbine engine according to claim 9 comprising a plurality of outlet guide vanes, and wherein the first component is an infill positioned between two adjacent outlet guide vanes and the second component is a liner. 11. The gas turbine engine according to claim 10, wherein the infill has a forward end and a rearward end and a liner is positioned adjacent the infill at both the forward end and the rearward end, and the sealing strip and sealant is used to seal a gap between the infill and the liners at both the forward end and rearward end of the infill. 12. The gas turbine engine according to claim 10, wherein one or more drainage holes are provided in the liner and the sealing strip is provided as a plurality of strip members, the strip members being spaced so as to permit water to exit the drainage holes formed in the liner. 13. The gas turbine engine according to claim 1, wherein the first and/or second component is a moulded component. 14. The gas turbine engine according to claim 1, wherein the plurality of pockets are closed pockets. 15. A method of sealing a gap between two adjacent components of a bypass duct of a gas turbine engine, the two adjacent components each having a gas washed surface, the method comprising: positioning a sealing strip in the gap between the two adjacent components, the sealing strip made from a compressible material in the shape of a hollow tube; andinjecting a sealant in the gap between the two adjacent components on a gas washed side of the adjacent components so as to seal the gap from airflow through the bypass duct,wherein at least one of the adjacent components comprises a plurality of projections configured so as to compress the sealing strip in the gap and arranged so as to define a plurality of pockets in the sealing strip. 16. A gas turbine engine having a fan and a bypass duct for discharging airflow from the fan to generate engine thrust, the bypass duct comprising: a first component and a second component each having a gas washed surface, the first component being positioned adjacent the second component with a gap therebetween;a sealing strip made from a compressible material in the shape of a hollow tube, the sealing strip positioned in the gap between the first component and the second component distal to the gas washed surfaces of the first and second components; anda sealant positioned between the first and second component proximal to the gas washed surfaces of the first and second components, so as to seal the gap between the first component and the second component from airflow through the bypass duct,wherein the first or second component comprises a plurality of elongated flat ribs, each of the elongated flat ribs extending from the first or second component to a distal edge, whereby the elongate flat ribs are arranged so as to contact the sealing strip along an edge of the elongate flat ribs so as to define a plurality of pockets in the sealing strip. 17. A gas turbine engine having a fan and a bypass duct for discharging airflow from the fan to generate engine thrust, the bypass duct comprising: a first component and a second component each having a gas washed surface, the first component being positioned adjacent the second component with a gap therebetween;a sealing strip made from a compressible material in the shape of a hollow tube, the sealing strip positioned in the gap between the first component and the second component distal to the gas washed surfaces of the first and second components; anda sealant positioned between the first and second component proximal to the gas washed surfaces of the first and second components, so as to seal the gap between the first component and the second component from airflow through the bypass duct,wherein the first or second component comprises a support member extending from the first or second component to a distal end, the support member supporting a plurality of ribs that extend perpendicular to the support member so as to contact the sealing strip and define a plurality of pockets in the sealing strip.
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