Removable diffusion stage for gas turbine engine fuel nozzle assemblages
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-001/00
F02C-003/00
출원번호
UP-0378025
(2006-03-17)
등록번호
US-7690203
(2010-05-20)
발명자
/ 주소
Bland, Robert J.
출원인 / 주소
Siemens Energy, Inc.
인용정보
피인용 횟수 :
3인용 특허 :
6
초록▼
A gas turbine engine fuel nozzle assemblage (10) comprises a nozzle outer body (25) comprising a premixing section (23) and an interiorly disposed first fuel passageway (22) to supply fuel to the premixing section (23), and more interiorly a central channel (33) comprising an inlet (30) from an air
A gas turbine engine fuel nozzle assemblage (10) comprises a nozzle outer body (25) comprising a premixing section (23) and an interiorly disposed first fuel passageway (22) to supply fuel to the premixing section (23), and more interiorly a central channel (33) comprising an inlet (30) from an air supply, an aperture (19) at an upstream end to receive a lance (18), and a downstream-disposed annular bearing surface (21) adapted to slidingly engage the lance, the fuel nozzle assemblage adapted so that the lance may be alternatably selected as any interchangeable one of a gas lance, an oil lance, and a non-fueling dummy lance. Between the lance and the central channel (33) is formed a cooling fluid passageway (24) that is in fluid communication with the inlet (30) and one or more cooling fluid passageway exits (60). The interchangeability of the lances (18) is effective to provide a desired flexible functionality to said fuel nozzle assemblage. The architecture of the fuel nozzle assemblage (10) may be utilized for higher level architectures of benefit to gas turbine engine facilities.
대표청구항▼
I claim as my invention: 1. A gas turbine engine fuel nozzle assemblage comprising: a nozzle outer body comprising a premixing section and an interiorly disposed first fuel passageway to supply fuel to said premixing section, and more interiorly a central channel comprising an inlet from an air sup
I claim as my invention: 1. A gas turbine engine fuel nozzle assemblage comprising: a nozzle outer body comprising a premixing section and an interiorly disposed first fuel passageway to supply fuel to said premixing section, and more interiorly a central channel comprising an inlet from an air supply, an aperture at an upstream end to removeably receive an interchangeable lance, and a downstream-disposed annular bearing surface adapted to slidingly engage the interchangeable lance, wherein said interchangeable lance is one of a gas lance, and an oil lance, wherein said interchangeable lance comprises a lance flange disposed proximate an interchangeable lance upstream end, wherein the interchangeable lance is removeably affixed proximate said aperture via the lance flange, and wherein said interchangeable lance within said central channel forms a cooling passageway, and said interchangeable lance is effective to provide a desired flexible functionality to said fuel nozzle assemblage. 2. The fuel nozzle assemblage of claim 1, wherein a fit between the interchangeable lance and the annular bearing surface thermally decouples the interchangeable lance from the nozzle outer body. 3. The fuel nozzle assemblage of claim 1, wherein the interchangeable lance is a gas lance. 4. A gas lance adapted for the fuel nozzle assemblage of claim 1. 5. A gas turbine engine nozzle assemblage comprising: a nozzle cuter body having an upstream end and a downstream end, comprising a radially disposed premixing section adapted to receive a first fuel through a first fuel passageway in the nozzle outer body, the nozzle outer body additionally comprising a first aperture at the upstream end and an annular bearing surface at the downstream end, wherein a removable and interchangeable lance inserted into the first aperture so as to contact the annular bearing surface defines an interior annular wall for a cooling fluid passageway for passage of tip cooling air; and said lance being one of a gas lance, and an oil lance, wherein said lance comprises a lance flange proximate a lance upstream end, wherein the lance is removeably fastened proximate the nozzle outer body upstream end via the lance flange. 6. A gas turbine engine combustor comprising a plurality of the nozzle assemblages of claim 5. 7. A gas turbine engine comprising a plurality of the nozzle assemblages of claim 5. 8. A gas turbine engine combustor architecture comprising: a nuzzle block comprising an outer surface, an inner surface disposed toward a combustor chamber space, and a plurality of passages between the outer surface and the inner surface aligned with a corresponding plurality of nozzle outer bodies, each said nozzle outer body extending into the combustor chamber space from the inner surface and each said nozzle outer body comprising a central channel configured to removably receive an interchangeable lance, wherein the lance is an oil lance, or a gas diffusion lance, and the lance is received through a corresponding one of said plurality of passages, and wherein the interchangeable lance comprises a lance flange disposed proximate an interchangeable lance upstream end, and wherein the lance flange is bolted into a fixed position with respect to an upstream end of the nozzle block via the lance flange. 9. An adaptable-mode fuel nozzle for a gas turbine engine, said nozzle comprising: an elongated first sleeve characterized by an upstream end and an opposite downstream end; a second sleeve disposed radially inward of said first sleeve, said first and second sleeves defining a first fuel passageway there between, said first fuel passageway including an inlet and an exit, said inlet being adapted for fluid communication with a first source of fuel and said exit disposed to provide said fuel to a premix nozzle section disposed radially outwardly of the first sleeve; a removable and interchangeable lance, said lance being one of a gas lance, and an oil lance, said lance comprising a lance flange proximate an lance upstream end via which the interchangeable lance is bolted to the fuel nozzle proximate the upstream end, the lance disposed radially inward of said second sleeve, said second sleeve and said lance defining a cooling fluid passageway there between, said cooling fluid passageway having an inlet and an exit; an annular bearing surface disposed about the fuel lance, effective to further define the cooling fluid passageway and to thermally decouple the fuel lance from the second sleeve to allow axial differential thermal growth there between; and a cooling fluid conduit adapted to fluidly connect said cooling fluid passageway with a source of cooling fluid, said conduit having a conduit entrance located upstream of said first fuel passageway exit and a conduit exit in fluid communication with said cooling fluid passageway inlet, whereby said cooling fluid conduit, said cooling fluid passageway, said lance and said first fuel passageway cooperatively ensure that cooling fluid passing through said cooling fluid passageway exit is substantially fuel-free during operation. 10. The adaptable-mode fuel nozzle of claim 9, wherein the first source of fuel is gaseous. 11. The adaptable-mode fuel nozzle of claim 9, wherein the lance is a gas lance, said gas lance additionally defining a central passageway therein, comprising an upstream-end inlet for receiving gas and a downstream-end outlet to provide said gas as a diffusion-type nozzle. 12. The adaptable-mode fuel nozzle of claim 10, wherein the lance is a gas lance, said gas lance additionally defining a central passageway therein, comprising an upstream-end inlet for receiving gas and a downstream-end outlet to provide said gas as a diffusion-type nozzle. 13. The adaptable-mode fuel nozzle of claim 9, wherein the lance is an oil lance, said oil lance additionally defining a central passageway therein, comprising an upstream-end inlet for receiving oil and a downstream-end outlet to provide said oil as a diffusion-type nozzle. 14. A gas turbine engine fuel nozzle comprising: a gas lance; and a nozzle outer body comprising a premixing section and an interiorly disposed first fuel passageway to supply fuel to said premixing section, and more interiorly a central channel comprising an inlet from an air supply, an aperture at an upstream end to removably receive said gas lance, and a downstream-disposed annular bearing surface adapted to slidingly engage said gas lance, wherein said gas lance, disposed within said central channel, forms a cooling passageway, and wherein said gas lance comprises a lance flange disposed proximate a gas lance upstream end, wherein the gas lance flange removeably affixes the gas lance upstream end to an upstream position fixed with respect to the upstream end of the nozzle outer body, and wherein said gas lance is effective to deliver gaseous fuel.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (6)
Fitts David O. (Charlton NY), Dry low NOx multi-nozzle combustion liner cap assembly.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.