Gas turbine engine thermally controlled flow device
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/20
F01D-017/08
F01D-017/14
F16K-031/00
G05D-023/02
출원번호
US-0105904
(2013-12-13)
등록번호
US-9562476
(2017-02-07)
발명자
/ 주소
Bastnagel, Thomas E.
출원인 / 주소
Rolls-Royce Corporation
대리인 / 주소
Fishman Stewart PLLC
인용정보
피인용 횟수 :
0인용 특허 :
13
초록▼
An apparatus includes a gas turbine engine flow device having an inner member and a surrounding member. The inner member has a first coefficient of thermal expansion; and the surrounding member at least partially surrounds the inner member and has a second coefficient of thermal expansion that is di
An apparatus includes a gas turbine engine flow device having an inner member and a surrounding member. The inner member has a first coefficient of thermal expansion; and the surrounding member at least partially surrounds the inner member and has a second coefficient of thermal expansion that is different from the first coefficient of thermal expansion. The surrounding member includes at least two walls that form a variable flow gap therebetween. The inner member is oriented relative to the at least two walls of the surrounding member such that, based on the difference in the first and second coefficients of thermal expansion, the inner member expands relatively greater than the surrounding member or the surrounding member expands relatively greater than the inner member, according to a temperature change to correspondingly enlarge or reduce the size of the variable flow gap between the at least two walls.
대표청구항▼
1. An apparatus comprising: a gas turbine engine flow device including an inner member and a surrounding member;the inner member having a first coefficient of thermal expansion; andthe surrounding member at least partially surrounding the inner member and having a second coefficient of thermal expan
1. An apparatus comprising: a gas turbine engine flow device including an inner member and a surrounding member;the inner member having a first coefficient of thermal expansion; andthe surrounding member at least partially surrounding the inner member and having a second coefficient of thermal expansion that is different from the first coefficient of thermal expansion of the inner member;the surrounding member including at least two walls that include a planar first wall and a cylindrical second wall that form a variable flow gap between an end of the second wall and an outer periphery of the first wall,wherein the inner member is oriented relative to the at least two walls of the surrounding member such that, based on the difference in the first and second coefficients of thermal expansion, the inner member expands relatively greater than the surrounding member or the surrounding member expands relatively greater than the inner member, according to a temperature change to correspondingly enlarge or reduce the size of the variable flow gap between the at least two walls. 2. The apparatus of claim 1, in which the inner member has a coefficient of thermal expansion that is greater than the coefficient of thermal expansion of the surrounding member, so that the inner member expands to exert a force against the at least two walls that urges apart the at least two walls relative to one another, which correspondingly enlarges the size of the variable flow gap between the at least two walls. 3. The apparatus of claim 1, in which the surrounding member has a coefficient of thermal expansion that is greater than the coefficient of thermal expansion of the inner member, so that the surrounding member expands to exert a force against the inner member that urges the at least two walls closer together, which correspondingly reduces the size of the variable flow gap between the at least two walls. 4. The apparatus of claim 1, in which the at least two walls close the variable flow gap in response to a temperature change that is an increase in temperature. 5. A gas turbine engine comprising: the apparatus of claim 1, wherein the gas turbine engine flow device is configured to change the area of the variable flow gap in proportion to the temperature change in the flow device. 6. An apparatus comprising: a gas turbine engine fluid adjusting device including a first member and a second member; andthe second member including opposing walls defining a flow path area therebetween, wherein one of the opposing walls is a planar wall and the other is a cylindrical wall,the first member being oriented relative to the opposing walls of the second member such that, based on dissimilar coefficients of thermal expansion of the first member and the second member, as temperature of the fluid changes, the first member urges ends of the opposing walls apart or the second member urges the ends of the opposing walls closer together, to change the flow path area between the opposing walls in a variable flow gap. 7. The apparatus of claim 6, in which the first member of the gas turbine engine fluid adjusting device has a coefficient of thermal expansion greater than the coefficient of thermal expansion of the second member. 8. The apparatus of claim 6, in which the opposing walls enlarge the flow path area in response to an increase in temperature. 9. The apparatus of claim 6, in which the opposing walls reduce the flow path area in response to an increase in temperature. 10. The apparatus of claim 9, in which the opposing walls close the flow path area in response to the increase in temperature. 11. A gas turbine engine comprising: the apparatus of claim 6; andthe gas turbine engine fluid adjusting device being configured to change the area of the variable flow gap in proportion to the temperature change in the gas turbine engine fluid adjusting device. 12. The apparatus of claim 11, in which the first member and the second member of the gas turbine engine fluid adjusting device interact to change the flow rate of the fluid in proportion to the change in temperature of the fluid. 13. The apparatus as claimed in claim 6, wherein the opposing walls form the variable flow gap therebetween. 14. A method of controlling fluid flow in a gas turbine engine fluid flow passage, comprising: passing fluid through a gas turbine engine flow control device in the gas turbine engine fluid flow passage at a flow rate at a first temperature, the flow control device including a first member and a second member, the first and second members including respectively a planar first wall and a cylindrical second wall that form opposing walls defining a flow path area between an end of the second wall and a periphery of the first wall, the first and second members having dissimilar coefficients of thermal expansion, andwherein the first member urges the opposing walls apart or the second member urges the opposing walls closer together when fluid flows through the flow control device at a second temperature, which changes the flow path area between the opposing walls based on the dissimilar coefficients of thermal expansion and changes a corresponding flow rate through the gas turbine engine fluid flow passage associated with the change in the flow path area. 15. The method of claim 14, in which the first member of the gas turbine engine flow control device has a coefficient of thermal expansion greater than the coefficient of thermal expansion of the second member of the gas turbine engine flow control device. 16. The method of claim 14, in which the second predetermined temperature is greater than the first predetermined temperature so that, based on the dissimilar coefficients of thermal expansion, the first member urges the opposing walls apart to enlarge the flow path area and the corresponding flow rate through the fluid flow passage in response to the increase in temperature. 17. The method of claim 14, in which the second predetermined temperature is greater than the first predetermined temperature so that, based on the dissimilar coefficients of thermal expansion, the second member urges the opposing walls closer together to reduce the flow path area and the corresponding flow rate through the fluid flow passage in response to the increase in temperature. 18. The method of claim 17, in which the opposing walls close the flow path area in response to the increase in temperature. 19. The method of claim 14, wherein the change in flow path area is in proportion to the temperature change in the gas turbine engine flow control device.
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