公开(公告)号：US11346282B2

公开(公告)日：2022-05-31

申请号：US16251492

申请日：2019-01-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Ramons A. Reba ,  Bruce L. Morin ,  Daniel L. Gysling ,  Carson A. Roy Thill ,  Jose R. Paulino ,  JinQuan Xu ,  Stephen A. Morford

IPC: F02C7/24 ,  F01D11/00 ,  F01D25/04 ,  G10K11/16

Abstract: A section for a gas turbine engine includes a rotating structure, a stationary structure, and a flow guide assembly arranged generally between the rotating structure and the stationary structure. A flow path is defined between the flow guide assembly and one of the rotating structure and the stationary structure. The flow guide assembly includes a plurality of apertures configured to disrupt acoustic waves of air in the flow path. A seal is configured to establish a sealing relationship between the rotating structure and the stationary structure, and wherein an inlet to the flow path is adjacent the seal. A gas turbine engine and a method of disrupting acoustic waves in a flow path of a gas turbine engine are also disclosed.

公开(公告)号：US10605087B2

公开(公告)日：2020-03-31

申请号：US15841627

申请日：2017-12-14

Applicant: United Technologies Corporation

Inventor： JinQuan Xu ,  Tracy A. Propheter-Hinckley

IPC: F01D5/14 ,  F01D5/28 ,  F01D11/14 ,  F01D11/08 ,  F01D25/00

Abstract: A turbomachine airfoil element has a substrate. The substrate defines an airfoil having a pressure side and a suction side. A plurality of fiber composite ribs are along the pressure side.

公开(公告)号：US20190390567A1

公开(公告)日：2019-12-26

申请号：US16014467

申请日：2018-06-21

Applicant: United Technologies Corporation

Inventor： JinQuan Xu ,  Glenn Levasseur

IPC: F01D25/12 ,  F01D5/18

Abstract: A gas turbine engine component according to an example of the present disclosure includes, among other things, a wall between first and second wall surfaces. The wall defines at least one cooling passage extending between an inlet along the first wall surface and an outlet along the second wall surface. The outlet has an upstream edge and a downstream edge with respect to a general direction of flow through the at least one cooling passage. The wall defines a plurality of crenellation features along at least the upstream edge. The upstream edge has a first profile established by the plurality of crenellation features, and the downstream edge has a second profile that differs from the first profile. A method of cooling is also disclosed.

公开(公告)号：US10464135B2

公开(公告)日：2019-11-05

申请号：US14771436

申请日：2014-03-11

Applicant: United Technologies Corporation

Inventor： JinQuan Xu

IPC: B22F7/08 ,  B23K26/342 ,  B23K15/00 ,  B23K26/00 ,  B28B1/00 ,  F01D5/18 ,  F01D9/06 ,  F23R3/00 ,  B33Y10/00 ,  B33Y40/00 ,  B23K103/02 ,  B23K101/00 ,  B23K103/08 ,  B23K103/00

Abstract: A method for forming a diffusion cooling hole in a substrate includes removing material from the substrate to form a metering section having an inlet on a first side of the substrate and removing material from the substrate to form a diffusing section that extends between the metering section and an outlet located on a second side of the substrate generally opposite the first side. The method also includes forming a feature on a substrate surface within one of the metering section and the diffusing section. Forming the feature includes depositing a material on the substrate surface and selectively heating the material to join the material with the substrate surface and form the feature.

公开(公告)号：US10443428B2

公开(公告)日：2019-10-15

申请号：US15111531

申请日：2015-01-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： JinQuan Xu

IPC: F02C7/14 ,  F02C7/18 ,  F02C9/18 ,  B64D33/02 ,  F01D17/14 ,  F01D17/10 ,  F01D25/12 ,  F01D11/00 ,  F02C3/04

Abstract: A cooling system for a gas turbine engine comprises a passage capable of receiving cooling air, a compartment radially adjacent thereto and axially aligned therewith, an opening therebetween, a valve within the opening, and a heat exchanger received in the compartment. The valve is moveable between a maximum open position and a minimum open position for increasing or decreasing airflow from the passage into the compartment. At the valve minimum open position, a leakage path is provided between the passage and the compartment, whereby cooling air is capable of passing from the passage to the compartment and toward the heat exchanger at all valve positions. A gas turbine engine is also disclosed.

公开(公告)号：US10371052B2

公开(公告)日：2019-08-06

申请号：US14768798

申请日：2014-02-25

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： JinQuan Xu

IPC: F02C7/047 ,  F02C7/14 ,  F02C7/12 ,  F02K3/06 ,  F02C7/36 ,  F02C7/045

Abstract: A thermal management system for a gas turbine engine includes a heat exchanger in fluid communication with a geared architecture and a heating compartment.

公开(公告)号：US20190234231A1

公开(公告)日：2019-08-01

申请号：US16379869

申请日：2019-04-10

Applicant: United Technologies Corporation

Inventor： JinQuan Xu

IPC: F01D17/14 ,  F02C9/18 ,  F02C7/14 ,  F02C3/04 ,  F01D11/00 ,  F02C7/18 ,  F01D25/12 ,  F01D17/10

CPC classification number: F01D17/145 ,  B64D2033/024 ,  F01D11/003 ,  F01D17/105 ,  F01D25/12 ,  F02C3/04 ,  F02C7/14 ,  F02C7/18 ,  F02C9/18 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/213 ,  F05D2300/514 ,  Y02T50/675

Abstract: A cooling system for a gas turbine engine comprises a passage capable of receiving cooling air, a compartment radially adjacent thereto and axially aligned therewith, an opening therebetween, a valve within the opening, and a heat exchanger received in the compartment. The valve is moveable between a maximum open position and a minimum open position for increasing or decreasing airflow from the passage into the compartment. At the valve minimum open position, a leakage path is provided between the passage and the compartment, whereby cooling air is capable of passing from the passage to the compartment and toward the heat exchanger at all valve positions. A gas turbine engine is also disclosed.

公开(公告)号：US09975169B2

公开(公告)日：2018-05-22

申请号：US15026409

申请日：2014-10-01

Applicant: United Technologies Corporation

Inventor： JinQuan Xu

IPC: B22C9/10 ,  B22D17/20 ,  F23R3/28 ,  F23D11/38 ,  B22C9/24 ,  F02C7/236

CPC classification number: B22C9/10 ,  B22C9/103 ,  B22C9/24 ,  B22D17/20 ,  F02C7/2365 ,  F05D2230/211 ,  F05D2230/30 ,  F23D11/38 ,  F23R3/28 ,  F23R3/286

Abstract: A method of manufacturing a fuel component for a gas turbine engine combustor includes additive manufacturing a sacrificial core and manufacturing a fuel component body at least partially around the sacrificial core. The sacrificial core is at least partially removed to at least partially define an internal geometry of the fuel component. An additively manufactured sacrificial core for a fuel component of a gas turbine engine combustor includes a first structure and a second structure. The first structure at least partially defines a first passage of the fuel component. The second structure at least partially defines a second passage of the fuel component. The second structure at least partially surrounds the first structure.

公开(公告)号：US20180023475A1

公开(公告)日：2018-01-25

申请号：US15217381

申请日：2016-07-22

Applicant: United Technologies Corporation

Inventor： JinQuan Xu

IPC: F02C7/18 ,  F02C9/18 ,  F01D9/06 ,  F02C3/04 ,  F01D25/24

CPC classification number: F02C7/18 ,  F01D9/065 ,  F01D25/24 ,  F02C3/04 ,  F02C6/08 ,  F02C7/12 ,  F02C9/18 ,  F02K3/115 ,  F05D2220/32 ,  F05D2260/208 ,  F05D2270/303 ,  Y02T50/676

Abstract: A gas turbine engine includes a core nacelle and a core engine disposed in the core nacelle. The core engine includes at least a compressor section, a combustor section, and a turbine section, which define a core flowpath. A bypass duct is radially outwards of the core nacelle. A component is disposed in the core engine. A cooling cavity is disposed outside of the bypass duct. A heat pipe contains a working medium sealed therein. The heat pipe includes a first section configured to accept thermal energy and a second section configured to dissipate the thermal energy in the cooling cavity. A tap from at least one of the compressor section or the bypass duct is configured to provide bleed air to the cooling cavity and dissipate the thermal energy from the second section.

公开(公告)号：US20180010465A1

公开(公告)日：2018-01-11

申请号：US15207472

申请日：2016-07-11

Applicant: United Technologies Corporation

Inventor： JinQuan Xu

IPC: F01D5/18 ,  F23R3/00 ,  F04D29/58 ,  F04D29/52 ,  F01D25/24 ,  F04D29/32 ,  F01D9/04 ,  F04D29/54 ,  F23R3/04 ,  F01D25/12

CPC classification number: F01D5/186 ,  F01D9/023 ,  F01D9/041 ,  F01D9/065 ,  F01D11/08 ,  F01D25/12 ,  F01D25/24 ,  F02K1/822 ,  F04D29/324 ,  F04D29/522 ,  F04D29/542 ,  F04D29/545 ,  F04D29/582 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2250/11 ,  F05D2250/75 ,  F05D2260/202 ,  F05D2260/2212 ,  F23R3/002 ,  F23R3/04 ,  F23R3/06 ,  F23R2900/03041 ,  F23R2900/03042 ,  Y02T50/676

Abstract: A gas turbine engine component having a cooling passage includes a first wall defining an inlet of the cooling passage, a second wall generally opposite the first wall and defining an outlet of the cooling passage, a metering section extending downstream from the inlet, and a diffusing section extending from the metering section to the outlet. The metering section includes an upstream side and a downstream side generally opposite the upstream side. At least one of the upstream and downstream sides includes a first passage wall and a second passage wall where the first and second passage walls intersect to form a V-shape.