IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0212576
(2008-09-17)
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등록번호 |
US-8261554
(2012-09-11)
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발명자
/ 주소 |
- Bailey, Donald Mark
- Simmons, Scott R.
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출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
5 |
초록
A system, in one embodiment, includes a fuel nozzle tip retainer that includes a structural member having a geometry that blocks a tip insert from moving axially downstream of a fuel nozzle.
대표청구항
▼
1. A turbine system, comprising: a turbine;a combustor;a compressor; anda fuel nozzle, comprising: a tubular tip comprising a first tubular portion and a second tubular portion coupled together, wherein the first tubular portion comprises a first axial blocking feature, and the second tubular portio
1. A turbine system, comprising: a turbine;a combustor;a compressor; anda fuel nozzle, comprising: a tubular tip comprising a first tubular portion and a second tubular portion coupled together, wherein the first tubular portion comprises a first axial blocking feature, and the second tubular portion comprises a second axial blocking feature; anda diffusion tip insert disposed inside the tubular tip, wherein the diffusion tip insert comprises a plurality of diffusion ports, the plurality of diffusion ports is axially offset from a downstream end of the tubular tip, the first axial blocking feature is configured to block axial movement of the diffusion tip insert in an upstream direction relative to the fuel nozzle, and the second axial blocking feature is configured to block axial movement of the diffusion tip insert in a downstream direction relative to the fuel nozzle. 2. The turbine system of claim 1, wherein the first and second tubular portions are directly fixed to one another. 3. The turbine system of claim 2, wherein the first tubular portion is made of a first material, the second tubular portion is made of a second material, and the second material is configured to withstand higher temperatures than the first material. 4. The turbine system of claim 1, wherein the second axial blocking feature comprises an inner annular shoulder having a first annular surface at a first diameter, a second annular surface at a second diameter, and a third surface between the first and second annular surfaces, wherein the third surface is at an angle of about 90 degrees relative to an axis of the first and second diameters. 5. The turbine system of claim 1, wherein the first axial blocking feature comprises an inner annular tapered surface. 6. The turbine system of claim 1, wherein the turbine system comprises a vehicle or a power generator. 7. The turbine system of claim 1, wherein the fuel nozzle comprises a compressed air passage, a swozzle, a bellows tube, fuel passage, and a flow conditioner. 8. The turbine system of claim 1, wherein the fuel nozzle comprises a braze between the tubular tip and the diffusion tip insert. 9. The turbine system of claim 1, wherein the diffusion tip insert has a first axial end opposite from a second axial end, the first axial end is axially offset from the first axial blocking feature, and the second axial end directly abuts the second axial blocking feature. 10. A turbine system, comprising: a fuel nozzle tip assembly, comprising: a tubular tip comprising a first tubular portion and a second tubular portion coupled together, wherein the first tubular portion comprises a first axial blocking feature, and the second tubular portion comprises a second axial blocking feature; anda tip insert disposed inside the tubular tip, wherein the tip insert comprises a plurality of diffusion ports, the plurality of diffusion ports is axially offset from a downstream end of the tubular tip, the first axial blocking feature is configured to block axial movement of the tip insert in a first axial direction, and the second axial blocking feature is configured to block axial movement of the tip insert in a second axial direction opposite to the first axial direction. 11. The turbine system of claim 10, wherein the fuel nozzle tip assembly comprises a weld or braze between the tip insert and the tubular tip. 12. The turbine system of claim 10, wherein the first and second axial blocking features do not include a weld or braze. 13. The turbine system of claim 10, wherein the first and second tubular portions are directly fixed to one another, the first tubular portion is made of a first material, the second tubular portion is made of a second material, and the second material is configured to withstand higher temperatures than the first material. 14. The turbine system of claim 10, wherein the first and second tubular portions directly axially abut one another. 15. The turbine system of claim 14, wherein the first axial blocking feature comprises an inner annular tapered surface and the second axial blocking feature comprises an inner annular shoulder. 16. The turbine system of claim 10, comprising a fuel nozzle having the fuel nozzle tip assembly, a turbine engine having the fuel nozzle tip assembly, or a combination thereof. 17. A turbine system, comprising: a fuel nozzle tip assembly, comprising:a tubular tip comprising a first tubular portion and a second tubular portion directly fixed to one another, wherein the first tubular portion is made of a first material, the second tubular portion is made of a second material, the second material is configured to withstand higher temperatures than the first material, and at least one of the first and second tubular portions comprises an axial blocking feature; anda diffusion tip insert disposed inside the tubular tip, wherein the diffusion tip insert comprises a plurality of diffusion ports, the plurality of diffusion ports is axially offset from a downstream end of the tubular tip, and the axial blocking feature is configured to block axial movement of the tip insert. 18. The turbine system of claim 17, wherein the plurality of diffusion ports comprises a first plurality of axial holes and a second plurality of crosswise holes relative to a longitudinal axis of the fuel nozzle tip assembly. 19. The turbine system of claim 17, wherein the first tubular portion comprises a first axial blocking feature configured to block axial movement of the tip insert in a first axial direction, and the second tubular portion comprises a second axial blocking feature configured to block axial movement of the tip insert in a second axial direction opposite to the first axial direction. 20. The turbine system of claim 19, wherein the diffusion tip insert has a first axial end opposite from a second axial end, the first axial end is axially offset from the first axial blocking feature, and the second axial end directly abuts the second axial blocking feature. 21. The turbine system of claim 17, comprising a fuel nozzle having the fuel nozzle tip assembly, a turbine engine having the fuel nozzle tip assembly, or a combination thereof.
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