公开(公告)号：US11174788B1

公开(公告)日：2021-11-16

申请号：US16875604

申请日：2020-05-15

Applicant: General Electric Company

Inventor： Jacob Kittleson ,  Daniel R. Burnos

IPC: F02C7/12

Abstract: A core for use in cooling a component used in a rotary machine is provided. The core includes a passage including a divider separating a first inlet portion and a second inlet portion to define a split pass inlet, which is fluidly coupled to at least one first pass, at least one second pass, and at least one turn. The at least one first pass channels a flow of cooling fluid in a first direction from the split pass inlet. The at least one second pass channels the flow of cooling fluid in a second direction opposite the first direction. The at least one turn changes a direction of flow of the cooling fluid from the first direction to the second direction. The at least one first pass, the at least one second pass, and the at least one turn are arranged, such that the passage defines a serpentine passage.

公开(公告)号：US11149644B2

公开(公告)日：2021-10-19

申请号：US16360329

申请日：2019-03-21

Applicant: Raytheon Technologies Corporation

Inventor： Frederick M. Schwarz ,  John T. Schmitz

IPC: F02C7/18 ,  B64D33/12 ,  F02C7/12 ,  F02K3/077 ,  B64D33/10 ,  F01D25/14 ,  B64D33/08 ,  F01D25/08 ,  F02C7/14 ,  F02C7/32 ,  F02K3/105 ,  F02K3/115 ,  B64D33/02 ,  F28D21/00

Abstract: A heat exchange module is provided for a turbine engine. The heat exchange module includes a duct and a plurality of heat exchangers. The duct includes a flowpath defined radially between a plurality of concentric duct walls. The flowpath extends along an axial centerline through the duct between a first duct end and a second duct end. The heat exchangers are located within the flowpath, and arranged circumferentially around the centerline.

公开(公告)号：US11149641B2

公开(公告)日：2021-10-19

申请号：US16812807

申请日：2020-03-09

Applicant: Raytheon Technologies Corporation

Inventor： Joseph D. Evetts ,  William J. Riordan ,  Federico Papa

IPC: F02C7/12 ,  F02C7/18 ,  F02C6/08 ,  B64D29/00 ,  F01D25/24 ,  F02C3/04 ,  F02C9/18 ,  B64D13/08 ,  F01D11/24

Abstract: A method of cooling a gas turbine engine case assembly includes moving a fan air valve that is operatively connected to a pre-cooler having a bypass inlet that is configured to receive bypass air that bypasses a gas turbine engine core to facilitate a provision of bypass air through a fan air valve inlet to the bypass inlet to a first open position, in response to a core compartment temperature being greater than a target core compartment temperature. The method further includes bleeding the bypass air through a bypass outlet of the pre-cooler into a core compartment.

公开(公告)号：US11111856B2

公开(公告)日：2021-09-07

申请号：US16291719

申请日：2019-03-04

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Bryan William Olver

IPC: F02C7/12 ,  F01D25/28 ,  F01D25/12 ,  F02K3/06 ,  F01D25/02 ,  B64D33/00 ,  B64D15/02

Abstract: The turbofan engine can have a core engine, a bypass duct surrounding the core engine, an annular bypass flow path between the bypass duct and the core engine, and a plurality of core links extending across the bypass path and supporting the core engine relative to the bypass duct, and a fluid passage having a heat exchange portion in a given one of the core links, the heat exchange portion being configured for heat exchange with the bypass flow path, an inlet leading into the given core link and to the heat exchange portion, and an outlet extending from the heat exchange portion and out of the given core link.

公开(公告)号：US20210215063A1

公开(公告)日：2021-07-15

申请号：US16743435

申请日：2020-01-15

Applicant: United Technologies Corporation

Inventor： Robin Prenter ,  Timothy J. Jennings ,  Carey Clum

IPC: F01D25/00 ,  F02C7/12 ,  F02C7/30

Abstract: A gaspath component for a gas turbine engine includes a platform. A body extends outward from the platform and includes at least one internal cooling passage. The internal cooling passage includes at least one particulate redirection feature defined at an end of the body opposite the platform. The at least one particulate redirection feature includes a first face oblique to and facing an expected flow of fluid through the internal cooling passage and defines at least one corresponding opening.

公开(公告)号：US20210207542A1

公开(公告)日：2021-07-08

申请号：US16735212

申请日：2020-01-06

Applicant: Hamilton Sundstrand Corporation

Inventor： Debabrata Pal ,  Craig R. LeGros ,  Tom A. Utecht

IPC: F02C7/268 ,  H05K7/20 ,  F01D15/10 ,  F02C7/12

Abstract: A starter/generator arrangement includes a starter/generator, a power converter electrically connected to the starter/generator, and coolant circuit with a pump and a condenser in fluid communication with the power converter. The power converter is arranged to flow start mode electrical power in a first direction in a start mode and a second direction in a generate mode. The coolant circuit fluidly couples the pump to the condenser for storing heat in a coolant disposed within the coolant circuit while flowing the start mode electrical power in the first direction. Gas turbine engines and methods of cooling starter/generator arrangements are also described.

公开(公告)号：US11040372B2

公开(公告)日：2021-06-22

申请号：US16377730

申请日：2019-04-08

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: B32B5/18 ,  B32B5/20 ,  B32B15/01 ,  B05D7/22 ,  C23F17/00 ,  B23H9/00 ,  C25D7/00 ,  C23C4/129 ,  C23C4/134 ,  C23C24/02 ,  C23C14/16 ,  C22F1/18 ,  C22F1/16 ,  C22F1/10 ,  C22F1/08 ,  C22F1/06 ,  C22F1/04 ,  B05D7/14 ,  C22C1/08 ,  F02C7/12 ,  B23K26/40 ,  C22C14/00 ,  B22F3/26 ,  B22F7/08 ,  B29C45/14 ,  B23K26/361 ,  B29C70/68 ,  B23K26/362 ,  B33Y10/00 ,  B23K103/02 ,  B23K103/08 ,  B29K705/00 ,  B29K105/12 ,  B22F10/20

Abstract: A light weight component, the light weight component including: a metallic foam core formed into a desired configuration; an external metallic shell applied to an exterior surface of the metallic foam core after it has been formed into the desired configuration; an inlet opening and an outlet opening formed in the external metallic shell in order to provide a fluid path through the metallic foam core; and a thermoplastic material injected into the metallic foam core via the inlet opening.

公开(公告)号：US11033955B2

公开(公告)日：2021-06-15

申请号：US15723591

申请日：2017-10-03

Applicant: United Technologies Corporation

Inventor： Wayde R. Schmidt ,  Paul Sheedy

IPC: B22C9/10 ,  B22C9/12 ,  B22C9/24 ,  F01D5/18 ,  F01D25/12 ,  B28B7/34 ,  F02C7/12 ,  F01D11/08 ,  F01D5/20

Abstract: Aspects of the disclosure are directed to treating a substrate, the substrate including at least one of a refractory metal or a ceramic material, and depositing a media onto the treated substrate to generate a casting core. Embodiments include a fixture, a substrate located on the fixture, the substrate including at least one of a refractory metal or a ceramic material, and a delivery head that deposits media onto the substrate to generate a casting core. Aspects are directed to a core configured for casting a component, the core comprising: a substrate that includes at least one of a refractory metal or a ceramic material, and media deposited on the substrate, the media having a dimension within a range of between 0.5 and 500 micrometers.

公开(公告)号：US20210131336A1

公开(公告)日：2021-05-06

申请号：US17146127

申请日：2021-01-11

Applicant: Radical Combustion Technologies, LLC

Inventor： Randall R. RAYMER ,  Michael J. MANFREDI

IPC: F02B19/10 ,  F02F1/24 ,  F02F3/12 ,  F02M31/02 ,  F02B19/12 ,  F02B19/18 ,  F02F3/16 ,  F02F1/36 ,  F01P7/14 ,  F01P3/00 ,  F01P3/02 ,  F01P3/06 ,  F02F1/16 ,  F01N13/10 ,  F02M35/10 ,  F02M25/028 ,  F02C7/12

Abstract: Systems, apparatus, and methods described herein can overcome some of the disadvantages associated with existing internal combustion engines. In particular, systems, apparatus, and methods described herein relate to improving the combustion process of internal combustion engines through insert technologies, engine modifications, control technologies, and/or other methodologies.

公开(公告)号：US20210071580A1

公开(公告)日：2021-03-11

申请号：US16594146

申请日：2019-10-07

Applicant: United Technologies Corporation

Inventor： Allan N. Arisi ,  Tracy A. Propheter-Hinckley

IPC: F02C7/12 ,  F02C3/04

Abstract: A gas turbine engine article includes an article wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The article wall defines a cavity. A cooling passage network is embedded in the article wall between inner and outer portions of the article wall. The cooling passage network has an inlet orifice through the inner portion of the article wall to receive cooling air from the cavity, a plurality of sub-passages that extend axially from the at least one inlet orifice, at least one outlet orifice through the outer portion of the airfoil wall, and trip strips for mixing cooling air in the cooling passage network.