公开(公告)号：US20220242581A1

公开(公告)日：2022-08-04

申请号：US17720708

申请日：2022-04-14

Applicant: Raytheon Technologies Corporation

Inventor： Frederick M. Schwarz ,  Michael Winter

IPC: B64D13/08 ,  F02C7/141 ,  F02C7/16 ,  F02C9/18 ,  F25B9/14 ,  F25J3/04 ,  B01D45/08 ,  B01D53/00 ,  B03C1/28 ,  B64D27/12 ,  B64D33/08 ,  F01D15/00 ,  F01D25/12 ,  F02C6/08 ,  F02C7/143 ,  F02C7/18 ,  F02K3/06 ,  B64D13/06 ,  F17C7/02 ,  F17C7/04

Abstract: A ground-based cryogenic cooling system includes a means for cooling an airflow and producing chilled air responsive to a power supply. A liquid air condensate pump system is operable to condense the chilled air into liquid air and urge the liquid air through a feeder line. A cryogenic cartridge includes a coupling interface configured to detachably establish fluid communication with the feeder line and a cryogenic liquid reservoir configured to store the liquid air under pressure. The cryogenic cartridge can be coupled to a cryogenic liquid distribution system on an aircraft. The liquid air can be selectively released from the cryogenic cartridge through the cryogenic liquid distribution system for an aircraft use.

公开(公告)号：US11339723B2

公开(公告)日：2022-05-24

申请号：US14431839

申请日：2013-03-15

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  William G. Sheridan ,  Glenn Levasseur

IPC: F16H1/36 ,  F02C7/36 ,  F02C3/107 ,  B23P15/14 ,  F16H1/48 ,  F16H57/04

Abstract: A geared architecture for a gas turbine engine includes a central gear supported for rotation about the axis, a plurality of intermediate gears engaged with the central gear and a ring gear circumscribing the intermediate gears. A first flexible coupling is provided between an input shaft driven by a turbine section and the sun gear. The geared architecture provides a power density comprising a power measured in horsepower (HP) related to a weight of the geared architecture within a defined range that benefits overall engine weight and efficiency.

公开(公告)号：US11286883B2

公开(公告)日：2022-03-29

申请号：US16405149

申请日：2019-05-07

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  Christopher M. Dye ,  Steven B. Johnson ,  Frederick M. Schwarz

IPC: F02K3/06 ,  B64D27/26 ,  F02C7/36 ,  F02C3/107 ,  F01D5/06 ,  F01D25/24 ,  F01D25/28 ,  F02C7/20 ,  F02K1/15 ,  F02C9/20 ,  F02C9/18 ,  F01D9/02 ,  F01D15/12 ,  F01D1/12

Abstract: A gas turbine engine includes, among other things, a fan section including a fan rotor, a gear train defined about an engine axis of rotation, a high spool, and a low spool including a low pressure turbine that drives the fan rotor through the gear train. A static structure includes a first engine mount location and a second engine mount location.

公开(公告)号：US20210372349A1

公开(公告)日：2021-12-02

申请号：US17395553

申请日：2021-08-06

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  Christopher M. Dye ,  Steven B. Johnson ,  Frederick M. Schwarz

IPC: F02K3/06 ,  F02C9/20 ,  F02C9/18 ,  B64D27/26 ,  F02C7/36 ,  F02C3/107 ,  F01D5/06 ,  F01D9/02 ,  F01D15/12 ,  F01D25/24 ,  F01D25/28 ,  F02C7/20 ,  F02K1/15

Abstract: A gas turbine engine includes, among other things, a propulsor section including a rotor, a gear train, a low spool and a high spool. A static structure includes a first case and a second case. A mount system includes a forward mount and an aft mount arranged in a plane containing an engine axis of rotation. The forward mount is secured to the first case. The aft mount is secured to the second case.

公开(公告)号：US20210355866A1

公开(公告)日：2021-11-18

申请号：US17383512

申请日：2021-07-23

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz

IPC: F02C3/107 ,  F02C7/36 ,  F02K3/06

Abstract: A propulsor section includes a propulsor having a plurality of blades rotatable about an engine longitudinal axis. A compressor section includes a low pressure compressor and a high pressure compressor. A turbine section includes a low pressure turbine that drives the propulsor through an epicyclic gear arrangement, and includes a second turbine that drives the high pressure compressor. A power ratio is provided by the combination of a first power input of the low pressure compressor and a second power input of the high pressure compressor. The power ratio is defined by the second power input divided by the first power input. The power ratio is equal to, or greater than, 1.0 and less than, or equal to, 1.4.

公开(公告)号：US20210348556A1

公开(公告)日：2021-11-11

申请号：US17192039

申请日：2021-03-04

Applicant: Raytheon Technologies Corporation

Inventor： Frederick M. Schwarz ,  Daniel Bernard Kupratis

IPC: F02C3/107 ,  F01D25/16 ,  F02K3/06 ,  F02C7/36

Abstract: A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in the first direction.

公开(公告)号：US11072429B2

公开(公告)日：2021-07-27

申请号：US16152929

申请日：2018-10-05

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: B64D13/06 ,  B64D27/26 ,  F02K3/04 ,  F02C6/08 ,  F02C7/20

Abstract: A disclosed gas turbine engine includes a fan section delivering air into a compressor section. An environmental control system includes a higher pressure tap at a higher pressure location in the compressor section, and a lower pressure tap at a lower pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet, and having a second passage leading into a compressor section of a turbocompressor. The higher pressure tap leads into a turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. A combined outlet of the compressor section and the turbine section of the turbocompressor intermixes and passes downstream to be delivered to an aircraft use.

公开(公告)号：US20210010418A1

公开(公告)日：2021-01-14

申请号：US17038608

申请日：2020-09-30

Applicant: Raytheon Technologies Corporation

Inventor： Frederick M. Schwarz

IPC: F02C3/107 ,  F01D5/14 ,  F02K3/06

Abstract: A turbofan engine includes a fan section including a fan blade having a leading edge and hub to tip ratio of less than about 0.34 and greater than about 0.020 measured at the leading edge and a speed change mechanism with gear ratio greater than about 2.6 to 1. A first compression section includes a last blade trailing edge radial tip length that is greater than about 67% of the radial tip length of a leading edge of a first stage of the first compression section. A second compression section includes a last blade trailing edge radial tip length that is greater than about 57% of a radial tip length of a leading edge of a first stage of the first compression section.

公开(公告)号：US10830131B2

公开(公告)日：2020-11-10

申请号：US16225623

申请日：2018-12-19

Applicant: Raytheon Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F02C3/107 ,  F01D25/16 ,  F02K3/06 ,  F04D25/02 ,  F04D29/059 ,  F04D29/32 ,  F02C7/36 ,  F02C7/06

Abstract: A turbofan engine comprising a fan shaft configured to rotate about an axis of the engine. A fan drive gear system is configured to drive the fan shaft. A first spool comprises a high pressure turbine and a high pressure compressor. A second spool comprises a lower pressure turbine, a lower pressure compressor, and a shaft coupling the lower pressure turbine to the intermediate pressure compressor. The engine has a plurality of main bearings. The lower pressure compressor has a plurality of disks and a forward hub mounted to a forwardmost disk.

公开(公告)号：US20230383699A1

公开(公告)日：2023-11-30

申请号：US18107126

申请日：2023-02-08

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Daniel Bernard Kupratis

IPC: F02C7/36 ,  F02K3/06 ,  F02C3/107 ,  F01D1/26 ,  F01D15/12

CPC classification number: F02C7/36 ,  F02K3/06 ,  F02C3/107 ,  F01D1/26 ,  F01D15/12 ,  F05D2260/40311 ,  F05D2270/051

Abstract: A gas turbine engine includes a propulsor section including a propulsor, a compressor section including a first compressor and a second compressor, a geared architecture, a turbine section including a first turbine and a drive turbine, and a power density of greater than or equal to 4.75 and less than or equal to 5.5 lbf/in3, wherein the power density is a ratio of a thrust provided by the engine to a volume of the turbine section.