公开(公告)号：US09360215B2

公开(公告)日：2016-06-07

申请号：US13437247

申请日：2012-04-02

申请人： Crisen McKenzie ,  Timothy S. Snyder

发明人： Crisen McKenzie ,  Timothy S. Snyder

IPC分类号： F23R3/06 ,  F23R3/00 ,  F23R3/50

CPC分类号： F23R3/06 ,  F02C3/04 ,  F05D2220/32 ,  F23R3/007 ,  F23R3/50 ,  F23R2900/03041

摘要： A combustor includes a shell that at least partially defines a combustion chamber and a grommet mounted in the shell. The grommet has a body that defines a passage through the grommet that is operable to communicate air from outside the combustion chamber into the combustion chamber. The body carries a first surface, an opposite, second surface and a third surface that defines the passage and joins the first surface and the second surface. The third surface includes a bevel surface with respect to at least one of the first surface and the second surface.

摘要翻译： 燃烧器包括壳体，其至少部分地限定安装在壳体中的燃烧室和垫圈。 索环具有限定通过索环的通道的主体，其可操作以将空气从燃烧室的外部传递到燃烧室。 身体承载限定通道并连接第一表面和第二表面的第一表面，相对的第二表面和第三表面。 第三表面包括相对于第一表面和第二表面中的至少一个的斜面。

公开(公告)号：US20130340437A1

公开(公告)日：2013-12-26

申请号：US13531132

申请日：2012-06-22

申请人： Nurhak Erbas-Sen ,  James B. Hoke ,  Albert K. Cheung ,  Robert M. Sonntag ,  Timothy S. Snyder

发明人： Nurhak Erbas-Sen ,  James B. Hoke ,  Albert K. Cheung ,  Robert M. Sonntag ,  Timothy S. Snyder

IPC分类号： F23R3/02 ,  F02C3/00

CPC分类号： F23R3/06 ,  F05B2260/201 ,  F05B2260/202 ,  F23R3/002 ,  F23R3/04 ,  F23R3/10 ,  F23R3/50 ,  F23R2900/03041 ,  F23R2900/03044

摘要： A turbine engine combustor wall includes support shell and a heat shield. The support shell includes shell quench apertures, first impingement apertures, and second impingement apertures. The combustor heat shield includes shield quench apertures fluidly coupled with the shell quench apertures, first effusion apertures fluidly coupled with the first impingement apertures, and second effusion apertures fluidly coupled with the second impingement apertures. The shield quench apertures and the first effusion apertures are configured in a first axial region of the heat shield, and the second effusion apertures are configured in a second axial region of the heat shield located axially between the first axial region and a downstream end of the heat shield. A density of the first effusion apertures in the first axial region is greater than a density of the second effusion apertures in the second axial region.

摘要翻译： 涡轮发动机燃烧器壁包括支撑壳和隔热罩。 支撑壳包括壳体淬火孔，第一冲击孔和第二冲击孔。 燃烧器热屏蔽包括与壳体骤冷孔流体耦合的屏蔽骤冷孔，与第一冲击孔流体连接的第一渗出孔以及与第二冲击孔流体连接的第二渗出孔。 所述屏蔽骤冷孔和所述第一渗出孔构造在所述隔热罩的第一轴向区域中，并且所述第二渗出孔构造在所述隔热罩的第二轴向区域中，所述第二轴向区域轴向位于所述第一轴向区域和所述第一轴向区域的下游端之间 隔热板。 第一轴向区域中的第一渗出孔的密度大于第二轴向区域中的第二渗出孔的密度。

公开(公告)号：US20130025293A1

公开(公告)日：2013-01-31

申请号：US13194182

申请日：2011-07-29

申请人： Won-Wook Kim ,  James B. Hoke ,  Timothy S. Snyder

发明人： Won-Wook Kim ,  James B. Hoke ,  Timothy S. Snyder

IPC分类号： F02C1/06 ,  F23R3/20 ,  F23R3/06

CPC分类号： F23R3/06 ,  F23R3/08 ,  Y02T50/675

摘要： A combustor for a turbine engine includes a first liner defined about an axis with a first row of first combustion air holes, one of the first combustion air holes is defined along each of a multiple of fuel injector zero pitch lines. A second liner defined about the axis with a second row of second combustion air holes, each of the second combustion air holes circumferentially offset relative to each of the multiple of fuel injector zero pitch lines.

摘要翻译： 用于涡轮发动机的燃烧器包括围绕具有第一排第一燃烧空气孔的轴限定的第一衬套，沿着多个燃料喷射器零间距线中的每一个限定第一燃烧空气孔中的一个。 围绕所述轴限定第二排第二燃烧空气孔的第二衬套，每个所述第二燃烧空气孔相对于所述多个燃料喷射器零间距线中的每一个周向地偏移。

公开(公告)号：US20130000311A1

公开(公告)日：2013-01-03

申请号：US13170406

申请日：2011-06-28

申请人： Timothy S. Snyder

发明人： Timothy S. Snyder

IPC分类号： F02C7/22

CPC分类号： F23R3/343 ,  F23D2900/00015 ,  F23R3/14

摘要： A fuel injection array for a gas turbine engine includes a plurality of bluff body injectors and a plurality of swirler injectors. A control operates the plurality of bluff body injectors and swirler injectors such that bluff body injectors are utilized without all of the swirler injectors at least at low power operation. The swirler injectors are utilized at higher power operation.

摘要翻译： 用于燃气涡轮发动机的燃料喷射阵列包括多个非流线体喷射器和多个旋流喷射器。 控制器操作多个非流线体喷射器和旋流器喷射器，使得不使用旋流器喷射器的非流线型喷射器至少在低功率运行时被利用。 旋流器注射器在更高功率运行时被使用。

公开(公告)号：US20120045319A1

公开(公告)日：2012-02-23

申请号：US13283752

申请日：2011-10-28

申请人： Timothy S. Snyder ,  Francisco J. Cunha

发明人： Timothy S. Snyder ,  Francisco J. Cunha

IPC分类号： F01D25/12 ,  F01D25/24

CPC分类号： F01D25/30 ,  F02C7/18 ,  F02K1/822 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/67 ,  Y02T50/676

摘要： A system comprises a bypass duct, a turbine case, a turbine exhaust ring and a splash plate. The turbine case is formed along a radially inner margin of the bypass duct, and the turbine exhaust ring is coaxially disposed within the turbine case. The splash plate extends axially along the turbine exhaust ring, radially spaced between the turbine exhaust ring and the turbine case. There are cooling fluid apertures in the turbine case to provide cooling fluid flow from the bypass duct onto the splash plate, and impingement holes in the splash plate to provide impingement flow onto the turbine exhaust ring.

摘要翻译： 一种系统包括旁通管道，涡轮机壳体，涡轮排气环和飞溅板。 涡轮壳体沿着旁通管道的径向内缘形成，并且涡轮机排气环同轴地设置在涡轮机壳体内。 飞溅板沿着涡轮机排气环轴向延伸，在涡轮机排气环和涡轮机壳之间径向间隔开。 在涡轮壳体中存在冷却流体孔，以提供从旁路管道到飞溅板的冷却流体流，以及飞溅板中的冲击孔，以在涡轮机排气环上提供冲击流。

公开(公告)号：US07870737B2

公开(公告)日：2011-01-18

申请号：US11696766

申请日：2007-04-05

申请人： Timothy S. Snyder

发明人： Timothy S. Snyder

IPC分类号： F02C1/00 ,  F02G3/00

CPC分类号： F23R3/14

摘要： A gas turbine engine pilot assembly includes a swirler having high and low pressure sides. A hood at least partially encloses the swirler on the high pressure side. The hood is secured over the swirler, in one example. The hood includes an aperture creating a tortuous path from the high pressure side to the low pressure side through the swirler. The hood reduces the differential pressure across the swirler by reducing the velocity and pressure of the air before entering the swirler. In one example, the hood includes first and second spaced apart walls interconnected by a perimeter wall. The walls form a generally annular structure, in one example. At least one of the walls includes an array of apertures communicating with a cavity interiorly arranged within the walls upstream from the swirler. Air from the high pressure side flows through the apertures and is slowed before passing through the swirler and into a combustion chamber.

摘要翻译： 燃气涡轮发动机引导组件包括具有高低压侧的旋流器。 罩子至少部分地围绕高压侧的旋流器。 在一个例子中，罩子固定在旋流器上。 发动机罩包括一个通过旋流器产生从高压侧到低压侧的曲折路径的孔。 引擎罩通过降低进入旋流器之前的空气的速度和压力来降低旋流器上的差压。 在一个示例中，罩包括通过周边壁互连的第一和第二隔开的壁。 在一个示例中，壁形成大致环形的结构。 所述壁中的至少一个包括与内部布置在所述旋流器上游的壁内的空腔相连通的孔阵列。 来自高压侧的空气流过孔，并在通过旋流器并进入燃烧室之前减慢。

公开(公告)号：US20100287941A1

公开(公告)日：2010-11-18

申请号：US12466948

申请日：2009-05-15

申请人： Won-Wook Kim ,  Timothy S. Snyder

发明人： Won-Wook Kim ,  Timothy S. Snyder

IPC分类号： F02C1/00

CPC分类号： F23R3/06

摘要： A combustor for a gas turbine engine is provided. The combustor includes a forward bulkhead, an inner radial combustor wall, and an outer radial combustor wall. The bulkhead includes a plurality of circumferentially disposed injector apertures. The inner radial combustor wall includes a plurality of inner quench aperture sets. Each inner quench aperture set includes a first inner quench aperture and a second inner quench aperture separated from each other by an inner interset distance. Each inner quench aperture set is separated from an adjacent inner quench aperture set by an inner intraset distance. The inner intraset distance is different than the inner interset distance. The outer radial combustor wall includes a plurality of circumferentially disposed outer quench apertures. The outer radial combustor wall is disposed radially outside of the inner radial combustor wall, thereby defining an annular combustion region therebetween.

摘要翻译： 提供了一种用于燃气涡轮发动机的燃烧器。 燃烧器包括前舱壁，内径向燃烧器壁和外径向燃烧室壁。 隔板包括多个周向设置的喷射孔。 内径向燃烧器壁包括多个内部淬火孔组。 每个内部骤冷孔径组件包括第一内部淬火孔和第二内部淬火孔，其彼此间隔内部距离。 每个内部淬火孔径组件与通过内部入座距离设置的相邻内部淬火孔径分离。 内部距离与内部距离不同。 外径向燃烧器壁包括多个周向设置的外部淬火孔。 外径向燃烧器壁设置在径向内径向燃烧室壁的外侧，从而在其间形成环形燃烧区域。

公开(公告)号：US07475546B2

公开(公告)日：2009-01-13

申请号：US11231181

申请日：2005-09-20

申请人： Timothy S. Snyder ,  Christopher R. Brdar ,  John R. Buey

发明人： Timothy S. Snyder ,  Christopher R. Brdar ,  John R. Buey

IPC分类号： F02K3/10

CPC分类号： F23R3/20 ,  F02K3/10 ,  F05D2250/324

摘要： A gas turbine engine augmentor nozzle has an inlet for connection to an augmentor fuel conduit and an outlet for expelling a spray of fuel. A passageway between the inlet and outlet is at least partially bounded by outlet end surface portions diverging from each other. The nozzle may be used as a replacement for a non-divergent nozzle and may reorient a fuel jet centerline toward radial.

摘要翻译： 燃气涡轮发动机增压喷嘴具有用于连接到增压器燃料管道的入口和用于排出燃料喷雾的出口。 入口和出口之间的通道至少部分地由彼此分开的出口端面部分限定。 喷嘴可以用作非发散喷嘴的替代物，并且可以使燃料喷射中心线朝向径向重新定向。

公开(公告)号：US06810673B2

公开(公告)日：2004-11-02

申请号：US10440585

申请日：2003-05-19

申请人： Timothy S. Snyder

发明人： Timothy S. Snyder

IPC分类号： F02C100

CPC分类号： F23R3/002 ,  F23R3/06 ,  Y02T50/675

摘要： A combustor for a gas turbine engine includes inner and outer liners with a row 112, 114 of dilution air holes penetrating through each liner. The row 114 of holes in the outer liner 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. The row 112 of holes in the inner liner include dilution air holes circumferentially offset from the major outer holes 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 unique 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.

公开(公告)号：US06513329B1

公开(公告)日：2003-02-04

申请号：US09718572

申请日：2000-11-22

申请人： Timothy S. Snyder ,  William A. Sowa ,  Stephen A. Morford ,  Kevin J. Van Dyke

发明人： Timothy S. Snyder ,  William A. Sowa ,  Stephen A. Morford ,  Kevin J. Van Dyke

IPC分类号： F02C300

CPC分类号： F23D14/82 ,  F23C7/002 ,  F23C2900/07002 ,  F23D14/74 ,  F23D17/00 ,  F23D17/002 ,  F23D2206/10 ,  F23D2209/10 ,  F23D2209/20 ,  F23R3/12 ,  F23R3/286

摘要： A tangential entry premixing fuel injector (10) for a gas turbine engine combustor includes a pair of offset scrolls (18) whose ends define a pair of entry slots (36) for admitting primary combustion air tangentially into a mixing chamber (28) bounded by the scrolls (18) and by longitudinally spaced endplates (14, 16). An array of fuel injection passages (42) extends along the length of the slots. The passage array is configured to inject a primary fuel nonuniformly along the length of the air entry slots and to control the fuel penetration depth d in proportion to slot height R. The injector also includes a flame disgorging centerbody (48) having a bluff tip (54) longitudinally aligned with the injector's discharge plane (22) and a secondary fuel conduit (80) extending through the centerbody for discharging a secondary combustible fluid, preferably gaseous fuel, through a series of fuel discharge openings (84) in the tip (54). The flame disgorging centerbody improves fuel injector durability by resisting ingestion of combustion flame into the mixing chamber (28) and reliably disgorging any flame that is ingested. The controlled fuel penetration depth reinforces the flame disgorging capability of the centerbody by preventing fuel from penetrating into the slowly moving boundary layer attached to the centerbody (48). The bluff character of the centerbody, in combination with its longitudinal alignment with the fuel injector discharge plane, makes the centerbody capable of anchoring the flame at the discharge plane so that combustion occurs aft of the discharge plane where the combustion flame is unlikely to damage the scrolls or centerbody. Introduction of fuel or fuel and air through the openings in the bluff tip encourage the flame to become anchored to the tip and therefore spatially stabilizes the flame, resulting in additional attenuation of acoustic oscillations and further improved combustor durability. The longitudinally nonuniform injection of primary fuel compensates for any mixing nonuniformities attributable to the flame disgorging centerbody and therefore augments flame stability. The injector and an associated method of premixing fuel and air prior to combustion suppress formation of nitrous oxides, and improve the durability of both the injector and the combustor.