Combustion system including a transition piece and method of forming using a cast superalloy
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F23R-003/44
F01D-009/02
B22D-019/00
출원번호
US-0454785
(2012-04-24)
등록번호
US-9109447
(2015-08-18)
발명자
/ 주소
McMahan, Kevin Weston
Peck, Arthur
Vlessis, Nicholas
출원인 / 주소
General Electric Company
대리인 / 주소
McNees Wallace & Nurick LLC
인용정보
피인용 횟수 :
0인용 특허 :
16
초록▼
A combustion system including a transition piece and method of forming the transition piece using a cast nickel-based superalloy is provided. The transition piece includes a body defining a flowpath and enclosure, the body having a circular inlet section for receiving combustion product from the com
A combustion system including a transition piece and method of forming the transition piece using a cast nickel-based superalloy is provided. The transition piece includes a body defining a flowpath and enclosure, the body having a circular inlet section for receiving combustion product from the combustor and an outlet end for flowing the combustor products into a first stage nozzle of a gas turbine. The transition piece comprises a one-piece single casting construction of the circular inlet section, the body, and the outlet end. The transition piece is formed from a nickel-based superalloy. The transition piece has a thick-to-thin ratio of wall thickness of thick transition to wall thickness of thin transition of about 1.1 to about 2.5.
대표청구항▼
1. A transition piece for a gas turbine, the transition piece comprising: a body defining a flowpath and enclosure, the body having a rounded inlet section for receiving combustion products from a combustor and an outlet end for flowing the combustor products into a first stage nozzle of the gas tur
1. A transition piece for a gas turbine, the transition piece comprising: a body defining a flowpath and enclosure, the body having a rounded inlet section for receiving combustion products from a combustor and an outlet end for flowing the combustor products into a first stage nozzle of the gas turbine;wherein the transition piece comprises a one-piece cast construction of the rounded inlet section, the body and the outlet end, the transition piece being formed from a nickel-based superalloy;wherein the transition piece has a thick-to-thin transition ratio of about 1.1 to about 2.5, the thick-to-thin transition ratio defined by a wall thickness of a thick wall section over a wall thickness of a thin wall section; andwherein the transition piece has a length-to-diameter ratio of about 0.1 to about 0.9, the length-to-diameter ratio defined by a length between the thick wall section and the thin wall section over a diameter of the rounded inlet section. 2. The transition piece of claim 1, wherein the transition piece comprises a frame surrounding the outlet end, the frame being integrally cast with the transition piece during one-piece cast construction. 3. The transition piece of claim 1, wherein the transition piece comprises component hardware of the gas turbine, the component hardware comprising component hardware that is integrally cast with the transition piece. 4. The transition piece according to claim 3, wherein the component hardware comprises at least one mounting connector. 5. The transition piece of claim 1, wherein the thick-to-thin transition ratio further ranges from about 1.3 to about 2.2. 6. A method of forming a one-piece cast transition piece comprising: providing a transition piece pattern;dipping the transition piece pattern in a slurry material to build up the slurry material;firing the slurry material to produce a transition piece shell;introducing a molten material including molten metal to the transition piece shell;solidifying the molten material to form the one-piece cast transition piece having a rounded inlet section;wherein the transition piece has a thick-to-thin transition ratio of about 1.1 to about 2.5, the thick-to-thin transition ratio defined by a wall thickness of a thick wall section over a wall thickness of a thin wall section; andwherein the transition piece has a length-to-diameter ratio of about 0.1 to about 0.9, the length-to-diameter ratio defined by a length between the thick wall section and the thin wall section over a diameter of the rounded inlet section. 7. The method of claim 6, wherein the transition piece pattern comprises a wax, a foam, and combinations thereof. 8. The method of claim 6, wherein the slurry material is a ceramic. 9. The method of claim 6, wherein the molten metal comprises a nickel-based superalloy, cobalt-based superalloy, and combinations thereof. 10. The method of claim 6, wherein the transition piece has a length-to-diameter ratio of about 0.3 to about 0.8. 11. The method of claim 6, wherein the transition piece has a taper ratio defined by the thick-to-thin transition ratio of about 1.3 to about 2.2 over the length-to-diameter ratio of about 0.1 to about 0.9. 12. A combustion system comprising: a combustor;a transition piece comprising:a body defining a flowpath and enclosure, the body having a rounded inlet section for receiving combustion products from the combustor and an outlet end for flowing the combustor products into a first stage nozzle of a gas turbine;wherein the transition piece comprises a one-piece cast construction, the transition piece being formed from a nickel-based superalloy;wherein the transition piece has a thick-to-thin transition ratio of about 1.1 to about 2.5, the thick-to-thin transition ratio defined by a wall thickness of a thick wall section over a wall thickness of a thin wall section; andwherein the transition piece has a length-to-diameter ratio of about 0.1 to about 0.9, the length-to-diameter ratio defined by a length between the thick wall section and the thin wall section over a diameter of the rounded inlet section. 13. The combustion system of claim 12, wherein the transition piece comprises a frame surrounding the outlet end and the frame comprising part of the one-piece cast construction. 14. The combustion system of claim 12, wherein the transition piece comprises component hardware of the combustion system, the component hardware comprising component hardware that is integrally cast with the combustion liner. 15. The combustion system of claim 12, wherein the thick-to-thin transition ratio further ranges from about 1.3 to about 2.2.
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이 특허에 인용된 특허 (16)
Steber Charles E. (Scotia NY), Aft mounting system for combustion transition duct members.
Brown, Mark Roger; Fric, Thomas Frank; Johnson, Thomas Edward; Kolman, Anne Elizabeth, Combustion liner for gas turbine formed of cast nickel-based superalloy.
Farmer, Gilbert; Brown, Daniel D.; Rutherford, Myron E.; Vise, Steven C.; Martini, Jeffrey M., Gas turbine combustor liner with asymmetric dilution holes machined from a single piece form.
Stumpf, James Anthony; Duncan, Beverly Stephenson; Burrus, David Louis; Cooper, Clayton Stuart, Liner for a gas turbine engine combustor having trapped vortex cavity.
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