公开(公告)号：EP2236930A3

公开(公告)日：2013-07-31

申请号：EP10250651.6

申请日：2010-03-30

Applicant: United Technologies Corporation

Inventor： Snyder, Timothy S. ,  Low, Kevin J.

IPC: F23R3/06 ,  F23R3/50

CPC classification number: F23R3/06 ,  F23R3/50 ,  Y02T50/675

Abstract: A gas turbine engine has a combustor module (10) including an annular combustor having a liner assembly that defines an annular combustion chamber. The liner assembly includes an inner liner (32) and an outer liner (34) that circumscribes the inner liner (32). The inner liner (32) has a plurality of first combustion air admission holes (66) passing therethrough and the second liner (34) has a plurality of second combustion air admission holes (68) passing therethrough. Each of the first and the second combustion air admission holes (66,68) has a swirler (70,80) disposed therein.

公开(公告)号：EP2551592A2

公开(公告)日：2013-01-30

申请号：EP12178487.0

申请日：2012-07-30

Applicant: United Technologies Corporation

Inventor： Cunha, Frank J. ,  Snyder, Timothy S.

IPC: F23R3/00 ,  F23R3/14 ,  F23R3/06

Abstract: A combustor component (72,74) of a gas turbine engine includes a refractory metal core (RMC) microcircuit (90).

公开(公告)号：EP2290289A2

公开(公告)日：2011-03-02

申请号：EP10251531.9

申请日：2010-08-31

Applicant: United Technologies Corporation

Inventor： Snyder, Timothy S. ,  Kim, Won-Wook

IPC: F23R3/06 ,  F23R3/50

CPC classification number: F23R3/06 ,  F23R3/50 ,  Y02T50/675

Abstract: A gas turbine engine has a combustor module including an annular combustor (26) having a liner assembly that defines an annular combustion chamber (30) and includes a circumferential row of a plurality of relatively large combustion dilution air admission holes (116) and a circumferential row of a plurality of smaller quench air admission holes (120) disposed downstream with respect to the flow of combustion gas products. The plurality of quench air admission holes (120) are arranged with respect to the plurality of relatively large dilution air admission holes (116) disposed upstream thereof such that there is associated with each dilution air admission hole (116) a first quench air admission hole (120) and a second quench air admission hole (120), the first quench air admission hole (120) being offset laterally in a first lateral direction and the second quench air admission hole (120) being offset laterally in a second lateral direction opposite to the first direction.

Abstract translation: 燃气涡轮发动机具有燃烧器模块，该燃烧器模块包括环形燃烧器（26），该环形燃烧器具有限定环形燃烧室（30）的衬套组件，并且包括周向排的多个相对大的燃烧稀释空气进入孔（116） 多个更小的骤冷空气入口孔（120）相对于燃烧气体产物的流动设置在下游。 多个骤冷空气入口孔相对于设置在其上游的多个相对较大的稀释空气进入孔（116）布置，使得与每个稀释空气入口孔（116）相关联，第一骤冷空气入口孔 （120）和第二骤冷气体入口孔（120），所述第一骤冷空气进入孔（120）在第一横向方向上横向偏移，所述第二骤冷空气入口孔（120）在相反的第二横向方向上横向偏移 到第一个方向。

公开(公告)号：EP2236930A2

公开(公告)日：2010-10-06

申请号：EP10250651.6

申请日：2010-03-30

Applicant: United Technologies Corporation

Inventor： Snyder, Timothy S. ,  Low, Kevin J.

IPC: F23R3/06

CPC classification number: F23R3/06 ,  F23R3/50 ,  Y02T50/675

Abstract: A gas turbine engine has a combustor module (10) including an annular combustor having a liner assembly that defines an annular combustion chamber. The liner assembly includes an inner liner (32) and an outer liner (34) that circumscribes the inner liner (32). The inner liner (32) has a plurality of first combustion air admission holes (66) passing therethrough and the second liner (34) has a plurality of second combustion air admission holes (68) passing therethrough. Each of the first and the second combustion air admission holes (66,68) has a swirler (70,80) disposed therein.

Abstract translation: 燃气涡轮发动机具有包括具有限定环形燃烧室的衬套组件的环形燃烧器的燃烧器模块（10）。 衬套组件包括内衬（32）和环绕内衬（32）的外衬（34）。 内衬（32）具有穿过其中的多个第一燃烧空气进入孔（66），第二衬套（34​​）具有穿过其中的多个第二燃烧空气进入孔（68）。 第一和第二燃烧空气进入孔（66,68）中的每一个具有设置在其中的旋流器（70,80）。

公开(公告)号：EP1235032B1

公开(公告)日：2006-11-22

申请号：EP02251341.0

申请日：2002-02-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Snyder, Timothy S.

IPC: F23R3/06 ,  F23R3/00

CPC classification number: F23R3/002 ,  F23R3/06 ,  Y02T50/675

公开(公告)号：EP1235032A2

公开(公告)日：2002-08-28

申请号：EP02251341.0

申请日：2002-02-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Snyder, Timothy S.

IPC: F23R3/06

CPC classification number: F23R3/002 ,  F23R3/06 ,  Y02T50/675

Abstract: A combustor for a gas turbine engine includes inner and outer liners 32,34 with a row 112, 114 of dilution air holes penetrating through each liner. The row 114 of holes in the outer liner 34 comprise at least a set of large size, major outer holes 116 and may also include a set of smaller size minor outer holes 118 circumferentially intermediate neighboring pairs of the major outer holes 116. The row 112 of holes in the inner liner include dilution air holes circumferentially offset from the major outer holes 116 and may also include a set of minor holes 122 circumferentially intermediate major inner holes 120 . The major and minor holes admit respective major and minor jets of dilution air into the combustor. The distribution of major and minor holes and the corresponding major and minor dilution air jets helps to minimize NOx emissions and regulates the spatial temperature profile of the exhaust gases discharged from the combustor.

Abstract translation: 用于燃气涡轮发动机的燃烧器包括具有一排112,114的穿透每个衬套的稀释气孔的内衬和外衬32,34。 外衬套34中的孔114的行114包括至少一组大尺寸的主外孔116，并且还可以包括一组较小尺寸的小外孔118，周向上位于相邻的主外孔116对之间。行112 内衬里的孔中的孔包括从主外孔116周向偏移的稀释气孔，并且还可以包括一组在主内孔120周向中间的小孔122.主孔和次孔容纳稀释空气的主要和次要射流进入 燃烧器。 主孔和次孔的分布以及相应的主要和次要稀释空气喷射有助于最小化NOx排放并调节从燃烧器排出的废气的空间温度分布。

公开(公告)号：EP0849530A3

公开(公告)日：1999-06-09

申请号：EP97310464.9

申请日：1997-12-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Kramer, Stephen K. ,  Hauck, Stephen F. ,  Snyder, Timothy S. ,  Sowa, William A.

IPC: F23C7/00 ,  F23D17/00

CPC classification number: F23C7/002 ,  F05B2250/232 ,  F05B2250/322 ,  F23C2900/07002 ,  F23D17/002

Abstract: A tangential air entry fuel nozzle (10) has a combustor inlet port (20) to permit air and fuel to exit into a combustor (56). The port includes a convergent surface (116), a combustor surface, and a cylindrical surface (118) extending therebetween. The convergent surface extends a first distance along the longitudinal axis (26) of the nozzle, the cylindrical surface extends a second distance along the axis, and the second distance is at least 30% of the first distance.

公开(公告)号：EP0849530A2

公开(公告)日：1998-06-24

申请号：EP97310464.9

申请日：1997-12-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Kramer, Stephen K. ,  Hauck, Stephen F. ,  Snyder, Timothy S. ,  Sowa, William A.

IPC: F23C7/00 ,  F23D17/00

CPC classification number: F23C7/002 ,  F05B2250/232 ,  F05B2250/322 ,  F23C2900/07002 ,  F23D17/002

Abstract: A tangential air entry fuel nozzle (10) has a combustor inlet port (20) to permit air and fuel to exit into a combustor (56). The port includes a convergent surface (116), a combustor surface, and a cylindrical surface (118) extending therebetween. The convergent surface extends a first distance along the longitudinal axis (26) of the nozzle, the cylindrical surface extends a second distance along the axis, and the second distance is at least 30% of the first distance.

Abstract translation: 切向进气燃料喷嘴（10）具有燃烧器入口（20），以允许空气和燃料离开燃烧器（56）。 该端口包括会聚表面（116），燃烧器表面和在它们之间延伸的圆柱形表面（118）。 会聚表面沿着喷嘴的纵向轴线（26）延伸第一距离，圆柱形表面沿轴线延伸第二距离，第二距离为第一距离的至少30％。

公开(公告)号：EP2253887B1

公开(公告)日：2019-04-17

申请号：EP10163039.0

申请日：2010-05-17

Applicant: United Technologies Corporation

Inventor： Kim, Won-Wook ,  Snyder, Timothy S.

IPC: F23R3/06

公开(公告)号：EP2541150B1

公开(公告)日：2018-04-11

申请号：EP12173923.9

申请日：2012-06-27

Applicant: United Technologies Corporation

Inventor： Snyder, Timothy S.

IPC: F23R3/14 ,  F23R3/34

CPC classification number: F23R3/343 ,  F23D2900/00015 ,  F23R3/14

Abstract: A fuel injection array (40) for a gas turbine engine (10) includes a plurality of bluff body injectors (44) and a plurality of swirler injectors (42). A control (300) operates the plurality of bluff body injectors (44) and swirler injectors (42) such that the bluff body injectors (44) are utilized without all of the swirler injectors (42) at least at low power operation. The swirler injectors (42) are utilized at higher power operation.