公开(公告)号：DE69727899D1

公开(公告)日：2004-04-08

申请号：DE69727899

申请日：1997-12-22

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SNYDER TIMOTHY S ,  SOWA WILLIAM A ,  KRAMER STEPHEN K

IPC: F23C7/00 ,  F23D17/00

公开(公告)号：CA2225360A1

公开(公告)日：1998-06-20

申请号：CA2225360

申请日：1997-12-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HAUCK PETER F ,  KRAMER STEPHEN K

IPC: F23R3/12 ,  F02M61/16 ,  F23C7/00 ,  F23D11/12 ,  F23D11/36 ,  F23D14/02 ,  F23D17/00 ,  F23R3/28 ,  F23R3/30 ,  F23R3/14 ,  F23D14/62

Abstract: A centerbody for a tangential entry fuel nozzle comprising a longitudinal axis, a centerbody base, said centerbody base having at least one air supply port extending therethrough. A radially outer surface includes a frustum portion defining the outer surface of a frustum that is coaxial with the longitudinal axis and flares toward the frustum base thereof, and a cylindrical portion which is integral with the frustum portion and preferably defines the outer surface of a cylinder, said frustum portion being located between said cylindrical portion and said centerline. An internal passageway coaxial with the longitudinal axis and including a first cylindrical passage, a second cylindrical passage, and a tapered passage, each passage having a first end and a second end, said second cylindrical passage having a diameter greater than said first cylindrical passage, said second cylindrical passage communicating with said first cylindrical passage through said tapered passage, said first end of said tapered passage integral with said second end of said first cylindrical passage, said second end of said tapered passage integral with said first end of said second cylindrical passage, said first end of said tapered passage having a diameter equal to the diameter of the first cylindrical passage, and said second end of said tapered passage having diameter equal to the diameter of the second cylindrical passage. Each of said passages is coaxial with the longitudinal axis, said first cylindrical passage including a discharge orifice that is circular coaxial with said axis and located at the first end of said first cylindrical passage. An internal chamber is located between said centerbody base and said second end of said second cylindrical passage, said air supply ports communicating with said second cylindrical passage through said chamber A swirler coaxial with the axis is located within the chamber immediately adjacent the second end of the second cylindrical passage, and a fuel lance coaxial with said axis and extending through said centerbody base, said internal chamber, and said swirler terminating within said second cylindrical passage.

公开(公告)号：DE69720155T2

公开(公告)日：2003-09-25

申请号：DE69720155

申请日：1997-12-22

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KRAMER STEPHEN K ,  MORFORD STEPHEN A ,  GRAVES CHARLES B

IPC: F02C7/232 ,  F02C9/28 ,  F02M61/16 ,  F23C7/00 ,  F23D11/12 ,  F23D11/36 ,  F23D17/00 ,  F23R3/12 ,  F23R3/28 ,  F23R3/30 ,  F23R3/34

Abstract: A method for burning fuel in the combustor of a gas turbine engine with a premixing type of combustion which comprises providing a scroll swirler (14) having first and second endplates (16,18), the first endplate is spaced relation to the second endplate defining a substantially cylindrical mixing zone (28) therebetween, the second endplate having a combustor inlet port (20) extending therethrough, providing a centerbody (12) located within the mixing zone and having a radially outer surface that tapers toward the combustor inlet and extends substantially the entire length of the mixing zone, introducing a first portion of combustion air tangentially into the mixing zone substantially continuously along the length thereof, introducing a first portion of fuel into the combustion air as the combustion air is introduced into the mixing zone, mixing the combustion air and fuel by swirling the combustion air and fuel about the centerbody while flowing the combustion air and fuel towards the combustor inlet, flowing the first portion of combustion air into the combustor inlet, introducing a second portion of combustion air into the first portion radially inward thereof at the combustor inlet, the sum of the first and second portions of combustion air defining total airflow, and the second portion of combustion air equal to 85-89% of the total airflow, and burning the fuel external of the mixing zone.

公开(公告)号：RU2193686C2

公开(公告)日：2002-11-27

申请号：RU97121010

申请日：1997-12-19

Applicant: UNITED TECHNOLOGIES CORP ,  TATA DELAWARE

Inventor： SNYDER TIMOTHY S ,  KRAMER STEPHEN K ,  SOWA WILLIAM A

IPC: F02M61/16 ,  F23C7/00 ,  F23C7/02 ,  F02C7/232 ,  F23C99/00 ,  F23D11/12 ,  F23D11/36 ,  F23D17/00 ,  F23R3/12 ,  F23R3/28 ,  F23R3/30 ,  F23R3/34

Abstract: FIELD: power engineering. SUBSTANCE: proposed injector has longitudinal axis and two spiral elements with cylindrical dome, axial lines of elements being displaced relative to each other. Overlapping ends of elements form inlet slot to feed fuel-air mixture into injector. End face plate of combustion chamber is provided with central hole to feed fuel and air into combustion chamber while other opposite end face plate blocks area of injector flow. Spiral elements are secured between said end face plates. Central part is located between said elements coaxially relative to longitudinal axis and it has base with at least one hole to deliver air passing through hole and inner channel, and also truncated figure section and aerodynamically shaped inclined sections preventing formation of reverse flow and providing stabilization of flame between said end face plates. EFFECT: increased service life. 6 cl, 3 dwg

公开(公告)号：CA2225364A1

公开(公告)日：1998-06-20

申请号：CA2225364

申请日：1997-12-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SNYDER TIMOTHY S ,  KRAMER STEPHEN K ,  SOWA WILLIAM A

IPC: F02C7/232 ,  F02M61/16 ,  F23C7/00 ,  F23C7/02 ,  F23D11/12 ,  F23D11/36 ,  F23D17/00 ,  F23R3/12 ,  F23R3/28 ,  F23R3/30 ,  F23R3/34 ,  F23D14/62 ,  F23D14/02 ,  F23R3/16

Abstract: A method of reducing the tendency of the combustion flame to stabilize within the mixing zone of a tangential entry nozzle is disclosed which comprises mixing fuel and air in a mixing zone within a fuel nozzle assembly, thereby producing a first fu el/air mixture which is isolated from the combustion products by maintaining sufficient ly high axial velocities throughout the mixing zone and using a combination of a second internal passageway within a centerbody (either fueled or unfueled) and the surfaces of t he combustor inlet port

公开(公告)号：CA2225357A1

公开(公告)日：1998-06-20

申请号：CA2225357

申请日：1997-12-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KRAMER STEPHEN K ,  HAUCK PETER F

IPC: F23R3/12 ,  F02M61/16 ,  F23C7/00 ,  F23D11/12 ,  F23D11/36 ,  F23D17/00 ,  F23R3/28 ,  F23R3/30 ,  F23R3/14 ,  F23D14/02 ,  F23D14/62

Abstract: A centerbody for a tangential entry nozzle having a longitudinal axis and a radially outer surface including a frustum portion defining the outer surface of a frustum that is coaxial with the longitudinal axis and flares toward the frustum base th ereof, and a curved portion which is integral with the frustum portion and preferably defines a portion of the surface generated by rotating a circle which is tangent to the frustum po rtion and has a center which lies radially outward thereof about the longitudinal axis. Th e centerbody has a base which includes at least one air supply port extending ther ethrough, and an internal passageway. The frustum portion tapers towards a discharge orifi ce of the internal passageway, and terminates at the plane in which the discharge orifice is located. A fuel-lance that is coaxial with the axis and extends through the base and term inates within the internal passageway provides fuel to the air flow in the centerbody.

公开(公告)号：DE60306879D1

公开(公告)日：2006-08-31

申请号：DE60306879

申请日：2003-12-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SAMMANN BRADLEY C ,  TWELVES WENDELL V ,  KLEIN HARVEY L ,  JONES JAMES E ,  JONES GARY D ,  NORRIS JAMES W ,  KRAMER STEPHEN K ,  THONEBE DOUGLAS A

IPC: F02C5/12 ,  F02C3/16 ,  F02C5/02 ,  F02C5/04 ,  F02C5/11 ,  F02K3/06 ,  F02K3/075 ,  F02K7/02 ,  F02K7/075

公开(公告)号：DE69720155D1

公开(公告)日：2003-04-30

申请号：DE69720155

申请日：1997-12-22

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KRAMER STEPHEN K ,  MORFORD STEPHEN A ,  GRAVES CHARLES B

IPC: F02C7/232 ,  F02C9/28 ,  F02M61/16 ,  F23C7/00 ,  F23D11/12 ,  F23D11/36 ,  F23D17/00 ,  F23R3/12 ,  F23R3/28 ,  F23R3/30 ,  F23R3/34

Abstract: A method for burning fuel in the combustor of a gas turbine engine with a premixing type of combustion which comprises providing a scroll swirler (14) having first and second endplates (16,18), the first endplate is spaced relation to the second endplate defining a substantially cylindrical mixing zone (28) therebetween, the second endplate having a combustor inlet port (20) extending therethrough, providing a centerbody (12) located within the mixing zone and having a radially outer surface that tapers toward the combustor inlet and extends substantially the entire length of the mixing zone, introducing a first portion of combustion air tangentially into the mixing zone substantially continuously along the length thereof, introducing a first portion of fuel into the combustion air as the combustion air is introduced into the mixing zone, mixing the combustion air and fuel by swirling the combustion air and fuel about the centerbody while flowing the combustion air and fuel towards the combustor inlet, flowing the first portion of combustion air into the combustor inlet, introducing a second portion of combustion air into the first portion radially inward thereof at the combustor inlet, the sum of the first and second portions of combustion air defining total airflow, and the second portion of combustion air equal to 85-89% of the total airflow, and burning the fuel external of the mixing zone.

公开(公告)号：RU2196247C2

公开(公告)日：2003-01-10

申请号：RU97121297

申请日：1997-12-19

Applicant: UNITED TECHNOLOGIES CORP ,  TATA DELAWARE

Inventor： MORFORD STEPHEN A ,  KRAMER STEPHEN K ,  GRAVES CHARLES B

IPC: F02C9/28 ,  F02M61/16 ,  F02C7/232 ,  F23C7/00 ,  F23D11/12 ,  F23D11/36 ,  F23D17/00 ,  F23R3/12 ,  F23R3/28 ,  F23R3/30 ,  F23R3/34

公开(公告)号：CA2225337A1

公开(公告)日：1998-06-20

申请号：CA2225337

申请日：1997-12-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MORFORD STEPHEN A ,  KRAMER STEPHEN K ,  GRAVES CHARLES B

IPC: F02C7/232 ,  F02C9/28 ,  F02M61/16 ,  F23C7/00 ,  F23D11/12 ,  F23D11/36 ,  F23D17/00 ,  F23R3/12 ,  F23R3/28 ,  F23R3/30 ,  F23R3/34 ,  F23R3/14 ,  F23D14/02 ,  F23D14/62

Abstract: A method for burning fuel in the combustor of a gas turbine engine with a premixing type of combustion which comprises providing a scroll swirler having f irst and second endplates, the first endplate is spaced relation to the second endplate d efining a substantially cylindrical mixing zone therebetween, the second endplate having a combustor inlet port extending therethrough, providing a centerbody located with in the mixing zone and having a radially outer surface that tapers toward the combustor inlet and extends substantially the entire length of the mixing zone, introducing a first portion of combustion air tangentially into the mixing zone substantially continuously alon g the length thereof, introducing a first portion of fuel into the combustion air as t he combustion air is introduced into the mixing zone, mixing the combustion air and fuel by sw irling the combustion air and fuel about the centerbody while flowing the combustion air an d fuel towards the combustor inlet, flowing the first portion of combustion air into th e combustor inlet, introducing a second portion of combustion air into the first p ortion radially inward thereof at the combustor inlet, the sum of the first and second portions of combustion air defining total airflow, and the second portion of combustion air equal to 85-89% of the total airflow, and burning the fuel external of the mixing zone.