公开(公告)号：CA2225393A1

公开(公告)日：1998-06-20

申请号：CA2225393

申请日：1997-12-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SOWA WILLIAM A ,  SNYDER TIMOTHY S

IPC: F02C7/232 ,  F02C7/22 ,  F02M61/16 ,  F23C7/00 ,  F23C7/02 ,  F23D11/12 ,  F23D11/36 ,  F23D17/00 ,  F23R3/12 ,  F23R3/28 ,  F23R3/30 ,  F23R3/14 ,  F23D14/02 ,  F23D14/62

Abstract: A tangential air entry fuel nozzle has a combustor inlet port to permit air and fuel to exit into a combustor. The port includes a convergent surface, a combustor su rface, and a cylindrical surface extending therebetween. The convergent surface extends a f irst distance along the longitudinal axis of the nozzle, the cylindrical surface exte nds a second distance along the axis, and the second distance is at least 30% of the first di stance.

公开(公告)号：CA2225376A1

公开(公告)日：1998-06-20

申请号：CA2225376

申请日：1997-12-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SNYDER TIMOTHY S ,  SOWA WILLIAM A

IPC: F02C7/232 ,  F02C9/28 ,  F02M61/16 ,  F23C7/00 ,  F23C7/02 ,  F23C9/00 ,  F23D11/36 ,  F23D17/00 ,  F23R3/12 ,  F23R3/28 ,  F23R3/30 ,  F23R3/34 ,  F23R3/14 ,  F23D14/02 ,  F23D14/62

Abstract: A method of reducing pressure fluctuations in the combustor of a gas turbine engine resulting from the combustion of fuel and air therein comprises combustin g a fuel/air mixture in a combustor downstream of the exit plane of a fuel nozzle as sembly such that such recirculation zones generated by the fuel nozzle assembly are in spaced relation to the exit plane and the combustion products are isolated from the fue l and air in the mixing zone at all operating conditions of the engine.

公开(公告)号：CA2183753A1

公开(公告)日：1995-08-31

申请号：CA2183753

申请日：1995-02-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SNYDER TIMOTHY S ,  ROSFJORD THOMAS J ,  MCVEY JOHN B ,  HU AARON ,  SCHLEIN BARRY

IPC: F23C7/00 ,  F23D17/00 ,  F23R3/12

Abstract: A premix liquid fuel nozzle has longitudinal air entrance slots (24) into a cylindrical chamber (20). A centerbody (42) produces an axially increasing flow area toward the chamber outlet (32). Liquid fuel is atomized in a specified location (58) adjacent the conical centerbody (42). This area has a high axial shear velocity producing thorough vaporization and uniform mixing before combustion.

公开(公告)号：EP3060850A4

公开(公告)日：2016-12-21

申请号：EP14878606

申请日：2014-10-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SNYDER TIMOTHY S

IPC: F23R3/28 ,  F02C7/22 ,  F23R3/00 ,  F23R3/06 ,  F23R3/14 ,  F23R3/34 ,  F23R3/42 ,  F23R3/50

CPC classification number: F23R3/346 ,  F23R3/002 ,  F23R3/06 ,  F23R3/14 ,  F23R3/50 ,  Y02T50/675

Abstract: A combustor section for a gas turbine engine includes an outer wall assembly and an inner wall assembly inboard of the outer wall assembly to define an annular combustion chamber therebetween. A forward fuel injection system is in communication with the combustion chamber. A downstream fuel injection system is in communication with the combustion chamber through the outer wall assembly and a swirl mixer system in communication with the combustion chamber through the inner wall assembly.

公开(公告)号：EP3077728A4

公开(公告)日：2016-11-30

申请号：EP14883404

申请日：2014-12-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： TU JOHN S ,  SNYDER TIMOTHY S ,  HOKE JAMES B ,  BANGERTER JAMES P ,  DUHAMEL DENNIS J ,  BURNS DAVID A

IPC: F23R3/00 ,  F23R3/06

CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R2900/03041 ,  F23R2900/03044 ,  Y02T50/675

公开(公告)号：EP2946145A4

公开(公告)日：2016-09-28

申请号：EP13872043

申请日：2013-01-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SNYDER TIMOTHY S ,  HOKE JAMES B

IPC: F23R3/04 ,  F23R3/06

CPC classification number: F23R3/005 ,  F02C7/18 ,  F23R3/06 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

Abstract: In accordance with one aspect of the disclosure, a combustor is disclosed. The combustor may include a shell and a liner disposed within the shell. The combustor may further include a grommet at least partially defining a hole communicating through the shell and liner and a cooling channel communicating through the grommet.

公开(公告)号：EP3036482A4

公开(公告)日：2017-05-03

申请号：EP14838205

申请日：2014-08-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SNYDER TIMOTHY S ,  DAI ZHONGTAO ,  SMITH RANDOLPH J ,  KOPP-VAUGHAN KRISTIN

IPC: F23R3/36 ,  F02C7/22 ,  F23R3/28

CPC classification number: F23C1/08 ,  F23D14/48 ,  F23D2900/11101 ,  F23R3/286 ,  F23R3/36

Abstract: In various embodiments, a dual fuel nozzle (200) for use in a gas 200 turbine engine is provided. The nozzle may be configured to supply and gas and a liquid. The dual fuel nozzle (200) may include an interior wall (217). The interior wall (217) may include a shoulder (219). The shoulder (219) may include one or more gas ports (216). Gas may be discharged through the gas ports (216) and penetrate a mixing zone.

Abstract translation: 在各种实施例中，提供了用于气体涡轮机200中的双燃料喷嘴（200）。 喷嘴可以被构造成供应气体和液体。 双燃料喷嘴（200）可以包括内壁（217）。 内壁（217）可以包括肩部（219）。 肩部（219）可以包括一个或多个气体端口（216）。 气体可以通过气体端口（216）排出并穿过混合区域。

公开(公告)号：EP3099975A4

公开(公告)日：2016-12-21

申请号：EP15743529

申请日：2015-01-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KOSTKA STANISLAV ,  CUNHA FRANK J ,  HOKE JAMES B ,  SNYDER TIMOTHY S ,  CHEUNG ALBERT K ,  ADAMOPOULOS CHRISTOS

IPC: F23M5/00 ,  F02C7/12

CPC classification number: F23R3/005 ,  F02C7/18 ,  F02K1/822 ,  F05D2260/20 ,  F05D2260/201 ,  F23R3/007 ,  F23R3/06 ,  F23R2900/00017 ,  F23R2900/03041 ,  F23R2900/03044 ,  F23R2900/03045 ,  Y02T50/675

Abstract: A liner panel for a combustor of a gas turbine engine includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a cone shaped pin.

公开(公告)号：EP2904238A4

公开(公告)日：2016-07-06

申请号：EP13856137

申请日：2013-08-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  SNYDER TIMOTHY S ,  ERBAS-SEN NURHAK ,  WILLIAMS ALEXANDER W ,  MULE NICHOLAS

IPC: F23R3/06

CPC classification number: F23R3/06 ,  F02C7/18 ,  F23R3/002 ,  F23R3/005 ,  F23R3/16 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03043 ,  F23R2900/03044 ,  F23R2900/03045 ,  Y02T50/675

Abstract: A combustor liner which reduces cooling flow to a combustion chamber and augments pressure drop split between impingement holes and effusion holes is disclosed. The combustor liner may further include accelerating channels, trip strips, pedestals, and cone-shaped effusion holes to provide further cooling of the liner. The combustor liner may reduce NOx production and the temperature of the combustion chamber of a gas turbine engine or the like.

Abstract translation: 公开了一种减少到燃烧室的冷却流动并增加冲击孔和渗出孔之间的压降分配的燃烧器衬套。 燃烧器衬套还可以包括加速通道，跳闸条，基座和锥形排出孔，以提供衬套的进一步冷却。 燃烧器衬套可以减少燃气涡轮发动机等的NOx产生和燃烧室的温度。

公开(公告)号：EP3039345A4

公开(公告)日：2017-04-26

申请号：EP14859549

申请日：2014-08-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DAI ZHONGTAO ,  SMITH RANDOLPH J ,  KOPP-VAUGHAN KRISTIN ,  SNYDER TIMOTHY S ,  HAUTMAN DONALD J

IPC: F23R3/28 ,  F02C7/22 ,  F23R3/02 ,  F23R3/36

CPC classification number: F23R3/12 ,  F02C7/22 ,  F23D11/383 ,  F23D2900/11101 ,  F23R3/14 ,  F23R3/28 ,  F23R3/283 ,  F23R3/286 ,  F23R3/36 ,  Y02T50/675

Abstract: A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, said outer air swirler defines an outer annular air passage between an outer wall and an inner wall, the outer wall defines a convergent-divergent nozzle. An inner air swirler along the axis to define an annular liquid passage therebetween, the annular liquid passage terminates upstream of the convergent-divergent nozzle and an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler.

Abstract translation: 用于燃气涡轮发动机的燃烧器的燃料喷嘴包括沿着轴线的外部空气旋流器，所述外部空气旋流器限定外壁和内壁之间的外部环形空气通道，外壁限定会聚 - 扩散喷嘴。 沿着轴线形成内部空气旋流器以在它们之间限定环形液体通道，环形液体通道终止于会聚 - 发散喷嘴的上游，并且围绕外部空气旋流器和内部空气旋流器之间的轴线的环形燃料气体通道。