IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0094948
(2011-04-27)
|
등록번호 |
US-8727714
(2014-05-20)
|
발명자
/ 주소 |
- Snider, Raymond G.
- Morrison, Jay A.
|
출원인 / 주소 |
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
11 |
초록
▼
A method of forming and/or assembling a multi-panel outer wall (14) for a component (12) in a machine subjected to high thermal stresses comprising providing such a component (12) that includes an inner panel wall (16) having an outer surface, and an array of interconnecting ribs (38) on the outer s
A method of forming and/or assembling a multi-panel outer wall (14) for a component (12) in a machine subjected to high thermal stresses comprising providing such a component (12) that includes an inner panel wall (16) having an outer surface, and an array of interconnecting ribs (38) on the outer surface of the component (12). An intermediate panel (22) is provided and preferably preformed to a general outer contour of the component (12), and is positioned over the inner panel (16). An external pressure force is applied across a surface area of the intermediate panel (22) against the outer surface of the component (12) to contour the intermediate panel (22) according to a geometric configuration formed by the ribs (38) thereby forming cooling chambers (24) between the outer surface and ribs (38) of the component (12) and the intermediate panel (22).
대표청구항
▼
1. A method of forming a multi-panel outer wall including an impingement cooling panel for components that are used under high thermally stressed conditions and having complex outer surface contours, comprising: providing a component to be incorporated in a machine and perform in an environment of h
1. A method of forming a multi-panel outer wall including an impingement cooling panel for components that are used under high thermally stressed conditions and having complex outer surface contours, comprising: providing a component to be incorporated in a machine and perform in an environment of high thermally stressed conditions and comprising an inner panel having an outer surface with an array of interconnecting ribs with a respective base disposed on the outer surface, said interconnecting ribs having a tapered cross-section such that a cross-sectional area at the base of the interconnecting ribs is larger than a cross-sectional area at an outer tip of the interconnecting ribs;positioning an intermediate panel over the inner panel to cover at least a portion of the outer surface and the interconnecting ribs of the inner panel;applying an external force under pressure across a surface area of the intermediate panel against the outer surface of the inner panel to contour the intermediate panel according to a geometric configuration formed by the interconnecting ribs, thereby forming cooling chambers between the outer surface and the interconnecting ribs of the inner panel and the intermediate panel; and,forming one or more holes in the intermediate panel and the inner panel to allow air flow into and out of the cooling chambers. 2. The method of claim 1, further comprising forming depressions in the intermediate panel between the interconnecting ribs. 3. The method of claim 1, wherein the applying external force under pressure to the intermediate panel comprises applying the external force at a predetermined pressure for a predetermined time duration. 4. The method of claim 1, further comprising positioning one or more inserts on the outer surface of the inner panel between interconnecting ribs and between the outer surface of the inner panel and the intermediate panel to form the cooling chambers having a volume determined by outer dimensions of the insert. 5. The method of claim 1, further comprising temporarily securing the intermediate panel along the interconnecting ribs of the inner panel before applying the external force under pressure. 6. The method of claim 1, further comprising forming the intermediate panel to coincide to an outer contour of the inner panel before applying the external pressure force. 7. The method of claim 1, wherein the step of providing the inner panel comprises providing a transition duct for a gas turbine engine and the inner panel having an inner surface defining a plenum through which air flows. 8. A method of assembling a component of a turbine machine, wherein the component is subject to high thermal stresses during operation of the turbine machine and comprises a multi-panel arrangement forming an air flow pattern for cooling the panels of the component, the method comprising: providing a component to be incorporated in a turbine engine and function in an environment of high thermally stressed conditions and having an inner panel with an outer surface and an array of interconnecting ribs with a respective base disposed on the outer surface, said interconnecting ribs having a tapered cross-section such that a cross-sectional area at the base of the interconnecting ribs is larger than a cross-sectional area at an outer tip of the interconnecting ribs;positioning an intermediate panel on the inner panel covering at least a portion of the outer surface of the inner panel and a portion of the interconnecting ribs on the inner panel;applying an external pressure force across a surface area of the intermediate panel at a predetermined pressure and for a predetermined time duration whereby first sections of the intermediate panel that contact respective interconnecting ribs on the inner panel conform to an outer geometric configuration of the interconnecting ribs and second sections of the intermediate panel between the first sections and the interconnecting ribs are spaced apart from the outer surface of the inner panel forming cooling chambers between interconnecting ribs, the inner panel and the intermediate panel, said second sections being spaced apart from the outer surface of the inner panel by a distance greater than a height of the interconnecting ribs from the outer surface of the inner panel; and,forming holes in the second sections of the intermediate panel and in the inner panel in fluid communication with the cooling chambers to allow air flow into and out of the cooling chambers. 9. The method of claim 8, further comprising securing the intermediate panel to the inner panel along the first sections of the intermediate panel and the interconnecting ribs. 10. The method of claim 8, further comprising positioning one or more inserts on the outer surface of the inner panel between the interconnecting ribs and between the outer surface of the inner panel and the intermediate panel to form the cooling chambers having a volume determined by outer dimensions of the insert. 11. The method of claim 8, wherein the applying an external pressure force comprises forming a depression on the second sections of the intermediate panel relative to the interconnecting ribs. 12. The method of claim 11, further comprising securing an outer panel to the intermediate panel along the first sections of the intermediate panel and wherein second sections of the outer panel are spaced apart from the second sections of the intermediate panel. 13. The method of claim 8, further comprising pre-forming the intermediate panel to coincide with a general outer contour of the inner panel before applying the external pressure force to the intermediate layer. 14. A component for a turbine machine wherein the component is subject to high thermal stresses during operation of the turbine machine and includes a multi-panel arrangement forming an air-flow pattern for cooling the panels of the component, the component comprising: an inner panel having an outer surface with an array of interconnecting ribs disposed thereon and extending radially outward from the outer surface;an intermediate panel secured to the inner panel along the interconnecting ribs whereby an external pressure force having been applied at a predetermined pressure for a predetermined time duration across a surface area of the intermediate panel thereby forming first sections of the intermediate panel that conform to an outer geometric configuration of the interconnecting ribs and forming second sections of the intermediate panel between the first sections and the interconnecting ribs, and the second sections of the intermediate panel are spaced apart from the outer surface of the inner panel forming cooling chambers between the interconnecting ribs, the outer surface of the inner panel and the second sections of intermediate panel, said second sections being spaced apart from the outer surface of the inner panel by a distance greater than a height of the interconnecting ribs from the outer surface of the inner panel; and,one or more holes formed in a plurality of the second sections of the intermediate panel and one or more holes formed in the outer surface of the inner panel between the interconnecting ribs to allow air flow into and out of the cooling chambers. 15. The component of claim 14, wherein the inner panel is a transition duct for a turbine machine that is disposed between a combustor and turbine blade stage of the turbine machine. 16. The component of claim 14, wherein the external pressure force is applied to the intermediate panel at the predetermined pressure and for the predetermined time duration so that the second sections of the intermediate panel are spaced from the outer surface of the inner panel between the interconnecting ribs a distance dimension that is less than a height dimension of the interconnecting ribs. 17. The component of claim 14, wherein the first sections of the intermediate panel thermally isolate the interconnecting ribs from air flowing in or through the cooling chambers. 18. The component of claim 14, wherein, before the external pressure force is applied to the intermediate panel, one or more inserts are removably positioned on the outer surface of the inner panel between interconnecting ribs and between the outer surface of the inner panel and the intermediate panel to form the cooling chambers having a volume determined by outer dimensions of the insert. 19. The component of claim 14, further comprising an outer panel secured to the inner panel and disposed over the intermediate panel and the outer panel includes first sections secured against the first sections of the intermediate panel and wherein second sections of the outer panel are spaced apart from the second sections of the intermediate panel forming an airflow path therebetween. 20. The component of claim 19, wherein a plurality of the second sections on the intermediate panel are depressed relative to the ribs on the inner panel thereby spacing the second sections of the intermediate panel and the outer panel forming the airflow paths therebetween. 21. The component of claim 14, wherein the component includes: an upper section including a two-layer system of the inner panel and the intermediate panel with the cooling chambers formed between the interconnecting ribs, the outer surface of the inner panel and the second sections of the intermediate panel; anda lower section downstream of the upper section, said lower section including a three-layer system including an outer panel secured to the inner panel and disposed over the intermediate panel; wherein the outer panel includes first sections secured against the first sections of the intermediate panel and wherein second sections of the outer panel are spaced apart from the second sections of the intermediate panel forming secondary cooling chambers between the section sections of the intermediate panel and the section sections of the outer panel.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.