Combustor dome assembly of a gas turbine engine having a free floating swirler
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F23R-003/60
F23R-003/00
출원번호
US-0638597
(2003-08-11)
발명자
/ 주소
McMasters,Marie Ann
Thompson,James Edward
Cimmarusti,Gregory Allen
Cooper,James Neil
Wiehe,Glenn Edward
출원인 / 주소
General Electric Company
인용정보
피인용 횟수 :
18인용 특허 :
12
초록▼
A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough, including: an annular dome plate having an inner portion, an outer portion, a forward surface and a plurality of circumferentially spaced openings formed therein, wherein a radial section
A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough, including: an annular dome plate having an inner portion, an outer portion, a forward surface and a plurality of circumferentially spaced openings formed therein, wherein a radial section is defined between adjacent openings; an annular outer cowl connected to the outer portion of the dome plate; an annular inner cowl connected to the inner portion of the dome plate; and, a swirler located between the forward surface of the dome plate and the inner and outer cowls in substantial alignment with each of the openings in the dome plate. Each swirler further includes a forward portion and an aft portion and is retained by at least one tab member located upstream thereof so as to be movable in a radial and axial direction.
대표청구항▼
What is claimed is: 1. A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough, comprising: (a) an annular dome plate having an inner portion, an outer portion, a forward surface and a plurality of circumferentially spaced openings formed ther
What is claimed is: 1. A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough, comprising: (a) an annular dome plate having an inner portion, an outer portion, a forward surface and a plurality of circumferentially spaced openings formed therein, wherein a radial section is defined between each adjacent opening; (b) an annular outer cowl connected to said outer portion of said dome plate; (c) an annular inner cowl connected to said inner portion of said dome plate; and, (d) a swirler located between said forward surface of said dome plate and said inner and outer cowls in substantial alignment with each of said openings in said dome plate; said swirler including: (1) a forward portion and an aft portion; and, (2) at least one tab located upstream of each said swirler for retaining said swirler with respect to said dome plate; wherein each said swirler is retained in a manner so as to be movable it a radial and axial direction. 2. The combustor dome assembly of claim 1, further comprising a first tab and a second tab located upstream of each said swirler for retaining said swirler with respect to said dome plate. 3. The combustor dome assembly of claim 2, wherein said first tabs are connected to said outer cowl and said second tabs are connected to said inner cowl. 4. The combustor dome assembly of claim 2, wherein said first tabs are formed integrally with said outer cowl and said second tabs are formed integrally with said inner cowl. 5. The combustor dome assembly of claim 2, wherein said first tabs are connected to said dome plate outer portion and said second tabs are connected to said dome plate inner portion. 6. The combustor dome assembly of claim 2, said first and second tabs each including an axial surface associated therewith for accommodating a predetermined amount of radial growth and movement by each said swirler forward portion therebetween. 7. The combustor dome assembly of claim 2, said first and second tabs each including an radial surface associated therewith and spaced from said dome plate forward surface for accommodating a predetermined amount of axial growth and movement by each said swirler. 8. A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough, comprising: (a) an annular dome plate having an inner portion, an outer portion, a forward surface and a plurality of circumferentially spaced openings formed therein, wherein a radial section is defined between each adjacent opening; (b) an annular outer cowl connected to said outer portion of said dome plate; (c) an annular inner cowl connected to said inner portion of said dome plate; (d) a swirler located between said forward surface of said dome plate and said inner arid outer cowls in substantial alignment with each of said openings in said dome plate, said swirler including a forward portion and an aft portion, wherein each said swirler is retained in a manner so as to be movable in a radial and axial direction; and (e) a deflector plate connected to and positioned within each opening in said dome plate, each said swirler aft portion including a lip which limits radial movement of each said swirler by engaging said deflector plate. 9. The combustor dome assembly of claim 1, further comprising a fuel nozzle positioned within a surface of each swirler, wherein each said swirler moves in conjunction with said fuel nozzle. 10. The combustor dome assembly of claim 1, said swirler aft portion including a flange which moves radially along said forward surface of said dome plate. 11. The combustor dome assembly of claim 1, wherein each said swirler includes vanes therein which are oriented to provide swirl in a substantially radial direction with respect to centerline axis through its associated dome plate opening. 12. The combustor dome assembly of claim 2, said swirler forward portion including a radial section which moves between said first and second tabs. 13. The combustor dome assembly of claim 2, said swirler forward portion including an axial section for receiving a fuel nozzle. 14. The combustor dome assembly of claim 1, further comprising an outer line connected to said dome plate outer portion and said outer cowl. 15. The combustor dome assembly of claim 1, further comprising an inner liner connected to said dome plate inner portion and said inner cowl.
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이 특허에 인용된 특허 (12)
Fortuna, Douglas M.; Houchens, William T.; Leonard, Gary L.; Napoli, Phillip D.; Sabla, Paul E.; Shafer, Douglas G.; Smith, Jr., Jack W., Anti-carboning fuel-air mixer for a gas turbine engine combustor.
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