公开(公告)号：US09896943B2

公开(公告)日：2018-02-20

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 ,  B22F5/04 ,  B22F3/105 ,  B22F5/00 ,  B22F7/00

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.

公开(公告)号：US20170284226A1

公开(公告)日：2017-10-05

申请号：US15085625

申请日：2016-03-30

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Shakeel Nasir ,  John Schugardt ,  Nick Nolcheff ,  John Meier ,  Yogendra Yogi Sheoran ,  Shezan Kanjiyani ,  Daniel Aukland

IPC: F01D25/32

CPC classification number: F01D25/32 ,  F02C7/36 ,  F04D29/441 ,  F04D29/701 ,  F05D2220/32 ,  F05D2250/52 ,  F05D2260/40311 ,  F05D2260/607 ,  Y02T50/675

Abstract: A turbine engine incorporating a fine particle separation means includes a radial compressor that rotates about a longitudinal axis, a radially-oriented diffuser located downstream and radially outward, with respect to the longitudinal axis, from the radial compressor, and a flow path positioned downstream and radially outward, with respect to the longitudinal axis, from the diffuser, wherein the flow path comprises an outer annular wall and an inner annular wall between which the compressed air flows, and wherein the flow path comprises an arc the redirects the compressed air from flowing in a substantially radial flow direction to a substantially axial flow direction. The turbine engine further includes an extraction slot in the outer annular wall that fluidly connects with a scavenge plenum, the scavenge plenum being positioned adjacent to and radially outward from the outer annular wall at a position downstream axially along the flow path from the arc.

公开(公告)号：US09702252B2

公开(公告)日：2017-07-11

申请号：US13719566

申请日：2012-12-19

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Shezan Kanjiyani ,  Natalie Wali ,  Don Mittendorf ,  Lorenzo Crosatti

IPC: F01D9/04 ,  F01D1/04 ,  B23P11/00

CPC classification number: F01D1/04 ,  B23P11/00 ,  F01D9/041 ,  F01D9/042 ,  F05D2230/60 ,  F05D2260/941 ,  Y02T50/671 ,  Y10T29/49245

Abstract: Embodiments of a turbine nozzle are provided, as are embodiments of methods for the manufacture of turbine nozzles. In one embodiment, the turbine nozzle includes a support ring and a slip joint ring, which is substantially concentric with the support ring and radially spaced apart therefrom. The slip joint ring has a plurality of slots therein. A plurality of vanes is fixedly coupled to the support ring and extends radially therefrom into the plurality of slots. A plurality of radial slip joints is formed between the plurality of vanes and the plurality slots. Each slip joint extends around a different one of the plurality of vanes to permit relative radial movement between the plurality of vanes and the slip joint ring during operation of the turbine nozzle.

公开(公告)号：US20150159495A1

公开(公告)日：2015-06-11

申请号：US14099218

申请日：2013-12-06

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Harry Lester Kington ,  Shezan Kanjiyani ,  Natalie Wali ,  John Gintert ,  Bradley R. Tucker

IPC: F01D9/04

CPC classification number: F01D9/042 ,  B22C9/04 ,  B22C9/22 ,  F01D9/041 ,  F01D25/26 ,  F05D2230/21 ,  F05D2300/50212

Abstract: Stationary airfoils configured to form an improved slip joint in bi-cast turbine engine components and the turbine engine components including the same are provided. The stationary airfoil for a bi-cast turbine engine component comprises a leading edge and a trailing edge interconnected by a pressure sidewall and a suction sidewall. An end portion is shaped with a pair of opposing flanges to form a slip joint with a shroud ring in the bi-cast turbine engine component and to define an interlocking feature. The slip joint permits radial movement of the stationary airfoil relative to the shroud ring due to thermal differential expansion and contraction.

Abstract translation: 提供了构造成在双流型涡轮发动机部件中形成改进的滑动关节的固定翼型件以及包括其的涡轮发动机部件。 用于双流型涡轮发动机部件的固定翼片包括通过压力侧壁和吸力侧壁互连的前缘和后缘。 端部形成有一对相对的凸缘，以在双流型涡轮发动机部件中形成具有护罩环的滑动接头并且限定互锁特征。 滑动接头允许固定翼型件相对于护罩环由于热差膨胀和收缩而径向移动。