公开(公告)号：US09988932B2

公开(公告)日：2018-06-05

申请号：US14099289

申请日：2013-12-06

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Ardeshir Riahi ,  Lorenzo Crosatti

IPC: F01D25/12 ,  F01D5/14 ,  F01D5/18 ,  F01D5/22 ,  F01D9/04 ,  F01D9/00

CPC classification number: F01D25/12 ,  F01D5/14 ,  F01D5/145 ,  F01D5/18 ,  F01D5/186 ,  F01D5/22 ,  F01D9/00 ,  F01D9/041 ,  F01D9/042 ,  Y02T50/673 ,  Y02T50/676

Abstract: Bi-cast turbine nozzles and methods for cooling the same are provided. The bi-cast turbine nozzle comprises an endwall. A vane is coupled to the endwall. The vane comprises an end portion and a leading edge and a trailing edge interconnected by a pressure sidewall and a suction sidewall. A slip joint is provided between the end portion and the endwall. A plurality of cooling holes is defined through the endwall. The plurality of cooling holes is disposed adjacent the periphery of the slip joint along the pressure sidewall of the vane and in proximity to the leading edge of the vane.

公开(公告)号：US09657642B2

公开(公告)日：2017-05-23

申请号：US14227924

申请日：2014-03-27

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Shezan Kanjiyani ,  John Gintert ,  Rajiv Rana ,  Lorenzo Crosatti ,  Bradley Reed Tucker ,  Ed Zurmehly

IPC: F02C7/18 ,  F01D25/12 ,  F01D25/14 ,  F01D5/18 ,  F01D11/08 ,  F02C3/10

CPC classification number: F02C7/18 ,  F01D5/187 ,  F01D11/08 ,  F01D25/12 ,  F01D25/14 ,  F02C3/10 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/205 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine section includes a stator assembly having an inner diameter end wall, an outer diameter end wall, and a stator vane; a turbine rotor assembly including a rotor blade extending into the mainstream gas flow path; a housing including an annular shroud that circumscribes the rotor blade and at least partially defines the mainstream hot gas flow path; a first baffle arranged to define a first cavity with the outer diameter end wall of the stator assembly; a second baffle; and a third baffle arranged to define a second cavity with the second baffle and a third cavity with the shroud. The first cavity is fluidly coupled to the second cavity and the second cavity is fluidly coupled to the third cavity such that cooling air flows from the first cavity to the second cavity and from the second cavity to the third cavity.

公开(公告)号：US09394798B2

公开(公告)日：2016-07-19

申请号：US13855417

申请日：2013-04-02

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Daniel Cregg Crites ,  Mark C. Morris ,  Lorenzo Crosatti ,  Ardeshir Riahi

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F01D5/186 ,  F05D2220/32 ,  F05D2240/121 ,  F05D2250/231 ,  F05D2250/232 ,  F05D2260/201 ,  Y02T50/671 ,  Y02T50/676

Abstract: An airfoil for a gas turbine engine is provided. The airfoil includes a body with a leading edge, a trailing edge, a first side wall extending between the leading edge and the trailing edge, and a second side wall extending between the leading edge and the trailing edge. The body defines an interior cavity. The airfoil includes an interior wall disposed within the interior cavity of the body and extending between the first wall and the second wall to define a supply chamber and a leading edge chamber. The interior wall defines a cooling hole with a base portion and a locally extended portion to direct cooling air from the supply chamber to the leading edge chamber such that the cooling air impinges upon the leading edge.

Abstract translation: 提供了一种用于燃气涡轮发动机的翼型件。 翼型件包括具有前缘的主体，后缘，在前缘和后缘之间延伸的第一侧壁，以及在前缘和后缘之间延伸的第二侧壁。 身体定义一个内腔。 所述翼型件包括设置在所述主体的内部空腔内并在所述第一壁和所述第二壁之间延伸的内壁，以限定供应室和前缘室。 内壁限定具有基部和局部延伸部分的冷却孔，以将冷却空气从供应室引导到前缘室，使得冷却空气撞击前缘。

公开(公告)号：US20150337680A1

公开(公告)日：2015-11-26

申请号：US14283104

申请日：2014-05-20

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Lorenzo Crosatti ,  Ardeshir Riahi ,  Bradley Reed Tucker ,  Shezan Kanjiyani

IPC: F01D25/12 ,  F01D9/02

CPC classification number: F01D9/02 ,  F01D9/04 ,  F01D9/042 ,  F01D9/065 ,  F01D25/12 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: Turbine nozzles and cooling systems for cooling slip joints therein are provided. The turbine nozzle has an endwall, a vane coupled to the endwall, a slip joint, and a plurality of airfoil quenching holes that cooperate with a plurality of endwall cooling holes. The vane comprises a leading edge and a trailing edge interconnected by a pressure sidewall and a suction sidewall and an end portion. The slip joint is between the end portion and the endwall. The airfoil quenching holes are defined through the pressure sidewall in the end portion. The endwall cooling holes are defined through the endwall along the pressure sidewall and in proximity to the leading edge. The airfoil quenching holes and endwall cooling holes are disposed adjacent the slip joint.

Abstract translation: 提供了用于冷却滑动接头的涡轮喷嘴和冷却系统。 涡轮喷嘴具有端壁，联接到端壁的叶片，滑动接头以及与多个端壁冷却孔配合的多个翼型骤冷孔。 叶片包括通过压力侧壁和吸力侧壁和端部部分互连的前缘和后缘。 滑动接头位于端部和端壁之间。 翼型淬火孔通过端部中的压力侧壁限定。 端壁冷却孔沿着压力侧壁并且靠近前缘限定通过端壁。 翼片淬火孔和端壁冷却孔设置在滑动接头附近。

公开(公告)号：US20150322800A1

公开(公告)日：2015-11-12

申请号：US14275012

申请日：2014-05-12

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Lorenzo Crosatti ,  Shezan Kanjiyani ,  Don Mittendorf

IPC: F01D5/18 ,  F01D5/14

CPC classification number: F01D5/189 ,  B22F3/1055 ,  B22F5/009 ,  B22F5/04 ,  B22F7/004 ,  F01D5/147 ,  F01D5/183 ,  F01D5/186 ,  F01D5/188 ,  F05D2260/202 ,  F05D2260/203 ,  Y02P10/295 ,  Y02T50/676 ,  Y10T29/49321

Abstract: Gas path components of gas turbine engines and methods for cooling the same using porous medium cooling systems are provided. The gas path component comprises a wall at least partially defining a cooling plenum and a porous medium cooling system. The wall includes a wall surface comprising a gas path surface and an opposing wall surface proximate the cooling plenum. The porous medium cooling system is disposed between the cooling plenum and the opposing wall surface. The porous medium cooling system comprises a perforated baffle and a porous material layer disposed between and adjacent the perforated baffle and the opposing wall surface. The wall includes a plurality of openings in fluid communication with the cooling plenum via the porous medium cooling system.

Abstract translation: 提供燃气涡轮发动机的气路部件和使用多孔介质冷却系统对其进行冷却的方法。 气体路径部件包括至少部分限定冷却气室和多孔介质冷却系统的壁。 该壁包括壁表面，该壁表面包括靠近冷却气室的气体通道表面和相对的壁表面。 多孔介质冷却系统设置在冷却气室和相对的壁表面之间。 多孔介质冷却系统包括穿孔挡板和设置在穿孔挡板和相对的壁表面之间和之间的多孔材料层。 该壁包括多个通过多孔介质冷却系统与冷却气室流体连通的开口。

公开(公告)号：US20150159513A1

公开(公告)日：2015-06-11

申请号：US14099289

申请日：2013-12-06

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Ardeshir Riahi ,  Lorenzo Crosatti

IPC: F01D25/12 ,  F01D5/18 ,  F01D9/04

CPC classification number: F01D25/12 ,  F01D5/14 ,  F01D5/145 ,  F01D5/18 ,  F01D5/186 ,  F01D5/22 ,  F01D9/00 ,  F01D9/041 ,  F01D9/042 ,  Y02T50/673 ,  Y02T50/676

Abstract: Bi-cast turbine nozzles and methods for cooling the same are provided. The bi-cast turbine nozzle comprises an endwall. A vane is coupled to the endwall. The vane comprises an end portion and a leading edge and a trailing edge interconnected by a pressure sidewall and a suction sidewall. A slip joint is provided between the end portion and the endwall. A plurality of cooling holes is defined through the endwall. The plurality of cooling holes is disposed adjacent the periphery of the slip joint along the pressure sidewall of the vane and in proximity to the leading edge of the vane.

Abstract translation: 提供双流透平喷嘴及其冷却方法。 双浇注涡轮喷嘴包括端壁。 叶片连接到端壁。 叶片包括端部和前缘以及通过压力侧壁和吸力侧壁相互连接的后缘。 在端部和端壁之间设置滑动接头。 通过端壁限定多个冷却孔。 多个冷却孔沿着叶片的压力侧壁并且靠近叶片的前缘设置在滑动接头的周边附近。