-
公开(公告)号：US20180266686A1
公开(公告)日：2018-09-20
申请号：US15365179
申请日：2016-11-30
Applicant: United Technologies Corporation
Inventor： Mark F. Zelesky , Randal G. McKinney
CPC classification number: F23R3/002 , F02C3/04 , F05D2220/323 , F05D2240/35 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044 , Y02T50/675
Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel including a liner panel with a perimeter rail and a multiple of intermediate rails. A combustor for a gas turbine engine including a support shell and a multiple of liner panels mounted to the support shell via a multiple of studs, each of the multiple of liner panels having a multiple of intermediate rails to form a multiple of circumferential cavities.
-
公开(公告)号：US10077666B2
公开(公告)日：2018-09-18
申请号：US14844082
申请日：2015-09-03
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , James D. Hill , Mark F. Zelesky
CPC classification number: F01D5/18 , F01D5/06 , F01D5/185 , F01D5/186 , F01D5/187 , F01D11/001 , F01D11/003 , F01D11/005 , F02C3/08 , F05D2220/32 , F05D2260/20 , Y02T50/676
Abstract: A turbine section includes a rotor assembly which includes an internal cooling passage. A segmented seal is adjacent the rotor assembly and includes a fluid passage that is in fluid communication with the internal cooling passage.
-
公开(公告)号：US09856793B2
公开(公告)日：2018-01-02
申请号：US14745564
申请日：2015-06-22
Applicant: United Technologies Corporation
Inventor： Mark F. Zelesky , Gabriel L. Suciu , Brian D. Merry
CPC classification number: F02C6/08 , F02C7/143 , F02K3/115 , F05D2260/211 , Y02T50/676
Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. The cooling compressor includes a downstream connection that delivers discharge pressure air to an upstream location in the high pressure turbine and a second tap from an intermediate pressure location within the cooling compressor. The second tap is connected to a downstream location within the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.
-
公开(公告)号：US20170211396A1
公开(公告)日：2017-07-27
申请号：US15143717
申请日：2016-05-02
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo , Parth Jariwala , Bret M. Teller , Mark F. Zelesky , James Tilsley Auxier
CPC classification number: F01D5/187 , F01D9/02 , F01D25/12 , F04D29/324 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2250/185 , F05D2260/202 , F05D2260/22141 , F05D2260/606 , Y02T50/676
Abstract: An airfoil of a gas turbine engine is provided including a leading edge extending in a radial direction, a tip extending in an axial direction from the leading edge, a first rib extending radially within the airfoil, the leading edge and the first rib defining a leading edge cavity within the airfoil, a second rib, the second rib and the first rib defining a serpentine cavity therein, a third rib extending axially within the tip, a flag tip cavity defined by the third rib, the leading edge, and the tip, the leading edge cavity fluidly connected to the flag tip cavity, and a bypass aperture formed between the first rib and the third rib, the bypass aperture configured to fluidly connect the serpentine cavity with the flag tip cavity.
-
公开(公告)号：US20170081959A1
公开(公告)日：2017-03-23
申请号：US15008148
申请日：2016-01-27
Applicant: United Technologies Corporation
Inventor： Scott D. Lewis , Mark F. Zelesky , Dominic J. Mongillo
Abstract: A gas turbine engine component having a cooling hole includes a first wall having a cooling hole inlet, a second wall generally opposite the first wall and having a cooling hole outlet, a metering section extending downstream from the inlet and having a hydraulic diameter (dh), and a diffusing section extending from the metering section to the outlet. The metering section includes a substantially convex first surface extending from a first end to a second end, a substantially concave second surface extending from a third end to a fourth end, and first and second curved portions connecting the ends of the first and second surfaces.
-
Patent Agency Ranking
公开(公告)号：US20160090844A1
公开(公告)日：2016-03-31
申请号：US14686945
申请日：2015-04-15
Applicant: United Technologies Corporation
Inventor： James T. Auxier , Parth Jariwala , Mark F. Zelesky , Bret M. Teller
IPC: F01D5/18
CPC classification number: F01D5/186 , F01D5/187 , F05D2250/185 , Y02T50/676
Abstract: A component for a gas turbine engine includes an exterior surface that provides pressure and suction sides. A cooling passage in the component includes a serpentine passageway that has first and second passes respectively configured to provide fluid flow in opposite directions from one another. The first pass includes first and second portions nested relative to one another and overlapping in a thickness direction. The first and second portions are adjacent to one another by sharing a common wall. The first portion is provided on the suction side. The second portion is provided on the pressure side.
Abstract translation: 用于燃气涡轮发动机的部件包括提供压力和吸力侧的外表面。 部件中的冷却通道包括蛇形通道，该蛇形通道具有分别配置成在彼此相反的方向上提供流体流动的第一和第二通道。 第一遍包括相对于彼此嵌套并在厚度方向上重叠的第一和第二部分。 第一和第二部分通过共享一个共同的墙壁彼此相邻。 第一部分设置在吸力侧。 第二部分设置在压力侧。
-
公开(公告)号：US20160024944A1
公开(公告)日：2016-01-28
申请号：US14775730
申请日：2014-02-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Ioannis Alvanos , Grant O. Cook, III , Mark F. Zelesky , Dilip M. Shah
CPC classification number: F01D5/30 , B23K20/16 , B23K2101/001 , F01D5/18 , F01D5/3061 , F02C3/04 , Y02T50/672
Abstract: A rotor assembly for a turbine engine includes a rotor disk constructed of a first material. Multiple rotor blades constructed of a second material are connected to the rotor disk via a diffusion material.
Abstract translation: 用于涡轮发动机的转子组件包括由第一材料构成的转子盘。 由第二材料构成的多个转子叶片通过扩散材料连接到转子盘。
-
公开(公告)号：US20150354465A1
公开(公告)日：2015-12-10
申请号：US14729002
申请日：2015-06-02
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , James D. Hill , Mark F. Zelesky
CPC classification number: F02C3/13 , F01D5/081 , F01D25/12 , F02C3/04 , F02C7/18 , F02C7/185 , F02C9/18 , F05D2260/213 , F05D2270/112 , F05D2270/20 , F05D2270/3032 , F05D2270/3062 , Y02T50/673 , Y02T50/676
Abstract: A turbine cooling air generation system for a gas turbine engine includes a first fluid pathway connecting a compressor bleed outlet and a mixing valve, a second fluid pathway connecting the compressor bleed outlet and an input of a heat exchanger, and a third fluid pathway connecting an output of the heat exchanger and the mixing valve. The mixing valve is further connected to an input of a turbine stage active cooling system.
Abstract translation: 一种用于燃气涡轮发动机的涡轮机冷却空气产生系统包括连接压缩机排气口和混合阀的第一流体路径，连接压缩机排气口和热交换器的输入口的第二流体路径，以及连接 输出热交换器和混合阀。 混合阀进一步连接到涡轮级主动冷却系统的输入端。
-
公开(公告)号：US20140140829A1
公开(公告)日：2014-05-22
申请号：US13679670
申请日：2012-11-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael F. Blair , Tracy A. Propheter-Hinckley , Mark F. Zelesky
IPC: F01D25/12
CPC classification number: F01D25/12 , F01D25/10 , F02C7/14 , F05D2260/205 , F05D2260/213 , F05D2260/232 , F28D15/00 , F28F1/124 , F28F1/40 , F28F7/02 , F28F2255/18 , Y02T50/676
Abstract: A turbine engine system includes a heat source, a heat exchanger, a cooling medium inlet and a cooling medium outlet. The heat source includes a first passage. The heat exchanger includes a second passage and a third passage. The first and the second passages are configured in a closed loop circuit. The third passage is configured between the inlet and the outlet in an open loop circuit.
Abstract translation: 涡轮发动机系统包括热源，热交换器，冷却介质入口和冷却介质出口。 热源包括第一通道。 热交换器包括第二通道和第三通道。 第一和第二通道配置在闭环回路中。 第三通道在开环电路中配置在入口和出口之间。
-
公开(公告)号：US10961854B2
公开(公告)日：2021-03-30
申请号：US16129457
申请日：2018-09-12
Applicant: United Technologies Corporation
Inventor： Timothy J. Jennings , Mark F. Zelesky
Abstract: A component for use in a gas turbine engine includes a channel configured to port a gas from an inlet along a flow path. The component further includes a wall defining an outlet configured to receive the gas, the wall forming an angle with the flow path that is between 60 degrees and 120 degrees, the outlet having a first portion with a first diameter and a second portion with a second diameter, the first portion configured to receive the gas before the second portion, and the first diameter being greater than the second diameter.
-
-
-
-
-
-
-
-
-
Search Results
120
records
(took 0.022 seconds)
