公开(公告)号：US20220364504A1

公开(公告)日：2022-11-17

申请号：US17320853

申请日：2021-05-14

Applicant: Raytheon Technologies Corporation

Inventor： Joseph B. Staubach ,  Marc J. Muldoon ,  James F. Wiedenhoefer

IPC: F02C1/04 ,  F28D1/047 ,  F28F9/013 ,  F28F9/02 ,  F28F1/02

Abstract: A heat exchanger for heat exchange between a first fluid and a second fluid has a plurality of tube sections, each having; an interior for passing the first fluid; an exterior for exposure to the second fluid; a first leg; a second leg; and a turn joining the first leg to the second leg. A has: fiber members passing between legs of the tube sections; and an end plate.

公开(公告)号：US20220136440A1

公开(公告)日：2022-05-05

申请号：US17085184

申请日：2020-10-30

Applicant: Raytheon Technologies Corporation

Inventor： Robert E. Malecki ,  Andrew Hahn ,  Marc J. Muldoon ,  Jesse M. Chandler ,  Joseph B. Staubach

IPC: F02C7/20 ,  F02C7/32 ,  F02C7/14 ,  B64D29/08 ,  B64D27/12 ,  F02C7/06

Abstract: A gas turbine engine and engine mount structure includes a core engine including a compressor section, a combustor section and a turbine section mounted within a core engine housing. The fan, the compressor section and the turbine section rotate about an axis of rotation. An outer nacelle surrounds the fan, and is spaced from the core engine housing to define a bypass duct. The fan delivers air into the bypass duct and into the core engine housing. The nacelle is formed with camber so as to be curved in a first plane away from the axis of rotation in a first lateral direction. An engine mount structure extends from the nacelle at an angle that is non-parallel and non-perpendicular to the first plane, and has a component in a lateral direction that is opposed to the first lateral direction. An aircraft is also disclosed.

公开(公告)号：US20220128003A1

公开(公告)日：2022-04-28

申请号：US17571720

申请日：2022-01-10

Applicant: Raytheon Technologies Corporation

Inventor： Marc J. Muldoon ,  Joseph B. Staubach ,  Jesse M. Chandler ,  Neil Terwilliger ,  Gabriel L. Suciu

IPC: F02C6/20 ,  F02C7/36

Abstract: An aircraft propulsion system includes a fan section that includes a fan shaft that is rotatable about a fan axis. The fan shaft includes a fan gear. The aircraft propulsion system also includes a boost turbine engine that includes a first output shaft that includes a first gear that is coupled to the fan gear. The boost turbine engine has a first maximum power capacity. The aircraft propulsion system further includes a cruise gas turbine engine that includes a second output shaft that includes a second gear that is coupled to the fan gear. The cruise turbine engine has a second maximum power capacity that is less than the first maximum power capacity of the boost turbine engine. The fan section produces a thrust that corresponds to power input through the fan gear from the boost turbine engine and the cruise turbine engine.

公开(公告)号：US20220074352A1

公开(公告)日：2022-03-10

申请号：US17530544

申请日：2021-11-19

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph B. Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C7/36 ,  F02C3/107 ,  F02C9/18 ,  F02K3/06 ,  F02K3/075 ,  F01D5/06 ,  F01D25/24 ,  F02C3/04 ,  F02C7/20 ,  F04D19/02 ,  F01D11/12

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor including a circumferential array of blades, a low pressure compressor section including a low pressure compressor section inlet with a low pressure compressor section inlet annulus area and a low pressure turbine section. The low pressure turbine section includes a maximum gas path radius, the blades include a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the blades is equal to or greater than 0.35, and is less than 0.55.

公开(公告)号：US11242805B2

公开(公告)日：2022-02-08

申请号：US16025022

申请日：2018-07-02

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph B. Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C7/36 ,  F02C3/107 ,  F02C9/18 ,  F01D11/12 ,  F01D5/06 ,  F01D25/24 ,  F02C3/04 ,  F02C7/20 ,  F04D19/02 ,  F02K3/075 ,  F02K3/06 ,  F04D29/32

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan including an array of fan blades rotatable about an engine axis, a compressor including a first compressor section and a second compressor section, the second compressor section including a second compressor section inlet with a compressor inlet annulus area, a fan duct including a fan duct annulus area outboard of the second compressor section inlet, and a turbine having a first turbine section driving the first compressor section, a second turbine section driving the fan through an epicyclic gearbox, the second turbine section including blades and vanes, and wherein the second turbine section defines a maximum gas path radius and the fan blades define a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the fan blades is less than 0.6.

公开(公告)号：US20210332759A1

公开(公告)日：2021-10-28

申请号：US16858858

申请日：2020-04-27

Applicant: Raytheon Technologies Corporation

Inventor： Lance L. Smith ,  Peter Cocks ,  Joseph B. Staubach

IPC: F02C7/224 ,  F02C3/04 ,  F02C3/24 ,  F23R3/30

Abstract: An energy extraction system according to an exemplary embodiment of this disclosure, among other possible things includes an ammonia fuel storage tank assembly that is configured to store a liquid ammonia fuel, a thermal transfer assembly that is configured to transform the liquid ammonia fuel into a vaporized ammonia based fuel, a turbo-expander that is configured to expand the vaporized ammonia based fuel to extract work, and an energy conversion device that is configured to use the vaporized ammonia based fuel from the turbo-expander to generate a work output.