Turbine nozzle components having reduced flow areas
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F04D-029/44
F01D-009/04
F01D-025/28
출원번호
US-0810802
(2015-07-28)
등록번호
US-9581035
(2017-02-28)
발명자
/ 주소
Macelroy, Bill
출원인 / 주소
HONEYWELL INTERNATIONAL INC.
대리인 / 주소
Lorenz & Kopf, LLP
인용정보
피인용 횟수 :
0인용 특허 :
20
초록▼
Embodiments of a method for controllably reducing of the flow area of a turbine nozzle component are provided, as are embodiments of turbine nozzle components having reduced flow areas. In one embodiment, the method includes the steps of obtaining a turbine nozzle component having a plurality of tur
Embodiments of a method for controllably reducing of the flow area of a turbine nozzle component are provided, as are embodiments of turbine nozzle components having reduced flow areas. In one embodiment, the method includes the steps of obtaining a turbine nozzle component having a plurality of turbine nozzle flow paths therethrough, positioning braze preforms in the plurality of turbine nozzle flow paths and against a surface of the turbine nozzle component, and bonding the braze preforms to the turbine nozzle component to achieve a controlled reduction in the flow area of the turbine nozzle flow paths.
대표청구항▼
1. A turbine nozzle component, comprising: an inner endwall;an outer endwall radially spaced from the inner endwall;a plurality of nozzle vanes extending between the inner and outer endwalls, the plurality of nozzle vanes having leading and trailing edges;a plurality of turbine nozzle flow paths ext
1. A turbine nozzle component, comprising: an inner endwall;an outer endwall radially spaced from the inner endwall;a plurality of nozzle vanes extending between the inner and outer endwalls, the plurality of nozzle vanes having leading and trailing edges;a plurality of turbine nozzle flow paths extending through the turbine nozzle component and generally defined by the inner endwall, the outer endwall, and the plurality of nozzle vanes; andbraze preforms positioned in the turbine nozzle flow paths and bonded to at least one of the inner endwall and outer endwall reducing the flow area of the turbine nozzle flow paths, the braze preforms wrapping around the leading and trailing edges of the plurality of nozzle vanes;wherein at least one of the braze preforms comprises a midline break dividing the braze preform into multiple pieces, which are bonded to one of the inner endwall and the outer endwall. 2. The turbine nozzle component of claim 1 wherein the braze preforms are further welded to at least one of the inner endwall and outer endwall. 3. The turbine nozzle component of claim 1 further comprising inner inter-blade flow areas provided on the inner endwall and bounding the plurality of flow paths, the plurality of braze preforms having planform geometries substantially conformal with the inner inter-blade flow areas. 4. The turbine nozzle component of claim 1 further comprising outer inter-blade flow areas provided on the outer endwall and bounding the plurality of flow paths, the plurality of braze preforms having planform geometries substantially conformal with the outer inter-blade flow areas. 5. The turbine nozzle component of claim 1 wherein the braze preforms are interspersed with the plurality of nozzle vanes. 6. The turbine nozzle component of claim 1 wherein the turbine nozzle component is produced from a parent superalloy, and wherein the plurality of braze preforms are each composed of a braze preform material comprising the parent superalloy and at least one melt point suppressant. 7. The turbine nozzle component of claim 6 wherein the braze preform material is substantially free of non-metallic components. 8. The turbine nozzle component of claim 1 wherein the braze preforms each comprise opposing sidewalls, which follow the contour of facing sidewalls of the plurality of nozzle vanes. 9. A turbine nozzle component, comprising: a first endwall;a second endwall radially spaced from the first endwall;nozzle vanes extending between the first and second endwalls;turbine nozzle flow paths extending through the turbine nozzle component and generally defined by the first endwall, the second endwall, and the nozzle vanes;inter-blade flow areas provided on the first endwall between the nozzle vanes and partially bounding the turbine nozzle flow paths; andbraze preforms bonded to the first endwall to reduce the flow area of the turbine nozzle flow paths, the braze preforms having planform geometries substantially conformal with the inter-blade flow areas and each comprising: an axially-elongated body; anda leading portion having an increased lateral width as compared to the axially-elongated body, the leading portion wrapping around a leading edge of at least one of the nozzle vanes. 10. The turbine nozzle component of claim 9 wherein the first endwall, the second endwall, and the turbine nozzle vanes are cast as a single piece from a master superalloy. 11. The turbine nozzle component of claim 10 wherein the braze preforms are composed of a braze preform material comprising the master alloy and a melt point suppressant. 12. The turbine nozzle component of claim 10 wherein the braze preforms are composed of a braze preform material comprising the master alloy and boron. 13. The turbine nozzle component of claim 9 wherein the braze preforms are composed of multiple layers of sintered braze tape. 14. The turbine nozzle component of claim 9 wherein the braze preforms each further comprise: a trailing portion having an increased lateral width as compared to the axially-elongated body, the trailing portion wrapping around a trailing edge of at least one of the nozzle vanes. 15. The turbine nozzle component of claim 9 wherein the braze preforms are resistance welded to the first endwall. 16. A turbine nozzle component, comprising: a cast body, comprising: a first endwall;a second endwall radially spaced from the first endwall; andnozzle vanes extending between the first and second endwalls, the nozzle vanes have a vane-to-vane spacing;turbine nozzle flow paths extending through the cast body and each including a vane metering point having a radial height; anda first plurality of braze preforms positioned within the turbine nozzle flow paths, bonded to the first endwall, and decreasing the radial heights of the vane metering points;wherein the first plurality of braze preforms each comprise: a curved body; andat least one widened portion extending from the curved body and having a lateral width exceeding the vane-to-vane spacing. 17. The turbine nozzle component of claim 16 further comprising inter-blade flow areas provided on the first endwall between the nozzle vanes and covered, at least in substantial part, by the braze preforms. 18. The turbine nozzle component of claim 16 further comprising a second plurality of braze preforms positioned within the turbine nozzle flow paths, bonded to the second endwall, and further decreasing the radial heights of the vane metering points. 19. The turbine nozzle component of claim 16 wherein the curved body of each of the first plurality of braze preforms comprises opposing sidewalls, which follow the contour of facing sidewalls of the nozzle vanes.
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