公开(公告)号：US4822244A

公开(公告)日：1989-04-18

申请号：US108528

申请日：1987-10-15

申请人： Mark S. Maier ,  Jesse Eng

发明人： Mark S. Maier ,  Jesse Eng

IPC分类号： F01D5/08 ,  F01D5/30

CPC分类号： F01D5/082 ,  F01D5/3015

摘要： The performance of a TOBI for a gas turbine engine is improved by providing bypass apertures in the housing of said TOBI for directing a stream of air into the seal sealing the TOBI compartment and bypassing the nozzles of the TOBI to reduce the size of the plume of the TOBI cooling air.

摘要翻译： 通过在所述TOBI的壳体中提供旁通孔来引导用于燃气涡轮发动机的TOBI的性能，用于将空气流引导到密封TOBI室中的密封件中并绕过TOBI的喷嘴，以减小TOBI的羽流的尺寸 TOBI冷却空气。

公开(公告)号：US5593112A

公开(公告)日：1997-01-14

申请号：US349844

申请日：1994-12-06

申请人： Mark S. Maier ,  Eric J. Gamble ,  Jack W. Wilson ,  Eliott L. Calzadilla ,  Gerald F. Goetz

发明人： Mark S. Maier ,  Eric J. Gamble ,  Jack W. Wilson ,  Eliott L. Calzadilla ,  Gerald F. Goetz

IPC分类号： F02K1/00 ,  F02K1/82 ,  B64C30/00

CPC分类号： F02K1/006 ,  F02K1/822 ,  Y02T50/675

摘要： The nacelle of the aircraft is purged and the sidewall of the vector nozzles of the gas turbine engine in the nacelle is cooled by utilizing the engine fan air to drive ejector pumps mounted in series flow relationship, a rectangular mixing zone and a diffuser with a rectangular cross section and a step in the exhaust nozzle gaspath. This results in minimizing the amount of fan air for driving the system and enhancing engine thrust and enhanced sidewall cooling because the temperature of the mixed air is lower than heretofore known systems.

摘要翻译： 吹扫飞机的机舱，并且通过利用发动机风扇空气来驱动机舱中的燃气涡轮发动机的矢量喷嘴的侧壁，以驱动以串联流动关系安装的喷射器泵，矩形混合区和具有矩形的扩散器 横截面和排气喷嘴气路中的一个步骤。 这导致最小化用于驱动系统的风扇空气量，并且由于混合空气的温度比迄今为止已知的系统低，因此增强发动机推力和增强的侧壁冷却。

公开(公告)号：US5022816A

公开(公告)日：1991-06-11

申请号：US427226

申请日：1989-10-24

申请人： Mark S. Maier ,  Jack W. Wilson, Jr.

发明人： Mark S. Maier ,  Jack W. Wilson, Jr.

IPC分类号： F01D9/02 ,  F01D11/08 ,  F01D25/24 ,  F02C7/20 ,  F02C7/28

CPC分类号： F01D11/08 ,  F01D25/246 ,  F05D2240/11

摘要： Tip shroud segments (26) are supported in support ring (24). The ring has at its downstream end conical surface (32) mating and in interference fit with conical surface (16). When flange (20) is torqued, face (22) aligns and forces support ring (24) into the interference fit. Concentricity and rigidity of the shroud support is obtained in a structure easily assembled and disassembled.

摘要翻译： 尖端护罩段（26）被支撑在支撑环（24）中。 环在其下游端锥形表面（32）配合并与锥形表面（16）过盈配合。 当法兰（20）被扭转时，面（22）对准并迫使支撑环（24）进入过盈配合状态。 在容易组装和拆卸的结构中获得护罩支撑件的同心度和刚性。

公开(公告)号：US20090180894A1

公开(公告)日：2009-07-16

申请号：US11971967

申请日：2008-01-10

申请人： Robert A. Brittingham ,  Mark S. Maier

发明人： Robert A. Brittingham ,  Mark S. Maier

IPC分类号： F01D5/18

CPC分类号： F01D5/225 ,  F05D2260/22141 ,  Y02T50/671 ,  Y02T50/676

摘要： A turbine blade that includes a tip shroud and one or more cooling cavities formed within the tip shroud. At least one of the cooling cavities may include a plurality of ribs and a first interior wall that generally opposes a second interior wall across the cooling cavity. The ribs may be configured such that some of the ribs originate on the first interior wall of the cooling cavity and extend toward the second interior wall of the cooling cavity and some of the ribs originate on the second interior wall of the cooling cavity and extend toward the first interior wall of the cooling cavity. And, the ribs that originate on the first interior wall of the cooling cavity and the ribs that originate on the second interior wall of the cooling cavity may have an alternating arrangement.

摘要翻译： 一种涡轮叶片，其包括尖端护罩和形成在尖端护罩内的一个或多个冷却腔。 至少一个冷却空腔可以包括多个肋和通过与冷却腔相对的第二内壁大致相对的第一内壁。 肋可以被配置成使得一些肋起源于冷却腔的第一内壁并且朝向冷却腔的第二内壁延伸，并且一些肋起源于冷却腔的第二内壁并且向着 冷却腔的第一内壁。 并且，起源于冷却腔的第一内壁的肋和起源于冷却腔的第二内壁上的肋可以具有交替排列。

公开(公告)号：US5603531A

公开(公告)日：1997-02-18

申请号：US349847

申请日：1994-12-06

申请人： Mark S. Maier

发明人： Mark S. Maier

IPC分类号： F02K1/80 ,  F02K1/82 ,  F16L27/02 ,  F23R3/48 ,  F61L27/04

CPC分类号： F16L27/026 ,  F02K1/80 ,  F02K1/822 ,  F23R3/48 ,  F05D2260/60 ,  Y02T50/675

摘要： The crossover tube conducts fluid from the exhaust nozzle of a gas turbine engine to a blind receiver mounted in the sidewall of the airframe when assembled and deployed and includes a rigidly affixed forward ball and joint and a ball attached to the ends of each of a pair of tubes mounted in telescopic relationship with a clip secured to the coverplate covering the ball at the forward end cooperating with a pair of end to end mounted coil springs surrounding the tubes to hold the crossover tube in an erect and extended position to be guided into the receiver of the sidewall when deployed. In another embodiment bellows are utilized in place of the coil springs to provent leakage of fluid flowing in the crossover tube.

摘要翻译： 交叉管将液体从燃气涡轮发动机的排气喷嘴传导到安装在机体的侧壁中的盲接收器，当组装和展开时，包括刚性固定的前球和接头以及连接到每一对的端部的球 与固定到盖板上的夹子以伸缩关系安装的管子，该夹子在前端处与围绕管子的一对端对端安装的螺旋弹簧配合，以将交叉管保持在直立和延伸位置，以引导到 部署时侧壁的接收器。 在另一个实施例中，使用波纹管代替螺旋弹簧以防止在交叉管中流动的流体泄漏。