公开(公告)号：US20240010351A1

公开(公告)日：2024-01-11

申请号：US17860746

申请日：2022-07-08

Applicant: Raytheon Technologies Corporation

Inventor： Brian M. Holley ,  Joseph B. Staubach ,  Marc J. Muldoon ,  Charles E. Lents

IPC: B64D37/30 ,  B64D41/00 ,  B64D15/12 ,  F02C3/22 ,  F02C7/32

CPC classification number: B64D37/30 ,  B64D41/00 ,  B64D15/12 ,  F02C3/22 ,  F02C7/32 ,  F05D2220/76 ,  F05D2220/323

Abstract: Aircraft propulsion systems include aircraft systems having at least one hydrogen tank and an aircraft-systems heat exchanger and engine systems having at least a main engine core, a high pressure pump, a hydrogen-air heat exchanger, and a turbo expander. The main engine core includes a compressor section, a combustor section having a burner, and a turbine section. Hydrogen is supplied from the at least one hydrogen tank through a hydrogen flow path, passing through the aircraft-systems heat exchanger, the high pressure pump, the hydrogen-air heat exchanger, and the turbo expander, prior to being injected into the burner for combustion. The turbo expander includes a rotor separated into a first expander portion and a second expander portion arranged about an output shaft and the output shaft is operably connected to a generator configured to generate electrical power.

公开(公告)号：US20230407768A1

公开(公告)日：2023-12-21

申请号：US18316505

申请日：2023-05-12

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Joseph B. Staubach

IPC: F01K15/02 ,  F02C7/16 ,  B01D53/26 ,  B01D45/16

CPC classification number: F01K15/02 ,  F02C7/16 ,  B01D53/265 ,  B01D2259/4575 ,  F05D2260/211 ,  B01D2257/80 ,  B01D45/16

Abstract: A propulsion system for an aircraft includes a gas generating core engine that generates an exhaust gas flow that is expanded through a turbine section. A power turbine engine is forward of the core engine and is coupled to drive a propulsor. A hydrogen fuel system supplies hydrogen fuel to the combustor through a fuel flow path. A condenser extracts water from the exhaust gas flow. A water separator is in communication with the condenser and directs the extracted water to a water storage tank. An evaporator receives a portion of the water that is extracted by the condenser and generates a steam flow. The steam flow is injected into the core flow path upstream of the turbine section.

公开(公告)号：US11846238B2

公开(公告)日：2023-12-19

申请号：US17060171

申请日：2020-10-01

Applicant: Raytheon Technologies Corporation

Inventor： Karl L. Hasel ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

IPC: F02C7/36 ,  F02K3/06 ,  F02C3/107 ,  F02C3/04 ,  F02K3/02 ,  F02C3/06

CPC classification number: F02C7/36 ,  F02C3/04 ,  F02C3/06 ,  F02C3/107 ,  F02K3/025 ,  F02K3/06 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2260/4031 ,  F05D2260/40311

Abstract: A turbofan gas turbine engine includes, among other things, a fan section, a core engine, a bypass passage, and a bypass ratio defined as the volume of air passing into the bypass passage compared to the volume of air passing into the core engine, the bypass ratio being greater than or equal to 10. A gear arrangement drives the fan section. A compressor section includes a low pressure compressor section and a high pressure compressor section. A turbine section drives the gear arrangement. An overall pressure ratio is provided by the combination of a pressure ratio across the low pressure compressor section and a pressure ratio across the high pressure compressor section, and greater than 40. The pressure ratio across the high pressure compressor section is between 7 and 15, and the pressure ratio across the low pressure compressor section is between 4 and 8.

公开(公告)号：US20230128287A1

公开(公告)日：2023-04-27

申请号：US17894587

申请日：2022-08-24

Applicant: Raytheon Technologies Corporation

Inventor： Amanda J. L. Boucher ,  Joseph B. Staubach

IPC: F02C3/22 ,  F02C7/06 ,  F02C7/22 ,  F02C7/224 ,  F02C7/36

Abstract: Turbine engine systems are described. The turbine engine systems include a combustor arranged along a core flow path of the turbine engine, a cryogenic fuel tank configured to supply a fuel to the combustor, a fuel supply line having a first flow supply line and a second flow supply line, the first flow supply line fluidly connecting the cryogenic fuel tank to the combustor through a first core flow path heat exchanger, and the second flow supply line fluidly connecting the cryogenic fuel tank to the combustor through a second core flow path heat exchanger, and a flow controller arranged along the fuel supply line and configured to respectively control a flow of fuel into the first flow supply line and the second flow supply line.

公开(公告)号：US20220412263A1

公开(公告)日：2022-12-29

申请号：US17896431

申请日：2022-08-26

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.

公开(公告)号：US20220349351A1

公开(公告)日：2022-11-03

申请号：US17840715

申请日：2022-06-15

Applicant: Raytheon Technologies Corporation

Inventor： Charles E. Lents ,  Joseph B. Staubach ,  Larry W. Hardin ,  Jonathan Rheaume

IPC: F02C7/36 ,  F01D15/10 ,  B64D31/06 ,  F02C6/14 ,  F02C9/50 ,  B64D27/24 ,  B64D27/10

Abstract: A gas turbine engine includes a core having a compressor section with a first compressor and a second compressor, a turbine section with a first turbine and a second turbine, and a primary flowpath fluidly connecting the compressor section and the turbine section. The first compressor is connected to the first turbine via a first shaft, the second compressor is connected to the second turbine via a second shaft, and a motor is connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft. The gas turbine engine includes a takeoff mode of operation, a top of climb mode of operation, and at least one additional mode of operation. The gas turbine engine is undersized relative to a thrust requirement in at least one of the takeoff mode of operation and the top of climb mode of operation, and a controller is configured to control the mode of operation of the gas turbine engine.

公开(公告)号：US11149650B2

公开(公告)日：2021-10-19

申请号：US16025038

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 ,  F04D29/54

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan including a circumferential array of fan blades, a compressor in fluid communication with the fan, the compressor including a first compressor section and a second compressor, the second compressor section including a second compressor section inlet with a second compressor section inlet annulus area, a fan duct including a fan duct annulus area outboard of the second compressor section inlet, a shaft assembly having a first portion and a second portion, a turbine in fluid communication with the combustor, the turbine having a first turbine section coupled to the first portion of the shaft assembly to drive the first compressor section, and a second turbine section coupled to the second portion of the shaft assembly to drive the fan, an epicyclic transmission coupled to the fan and rotatable by the second turbine section through the second portion of the shaft assembly to allow the second turbine to turn faster than the fan, wherein the second turbine section includes a maximum gas path radius and the fan blades include 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：US20210301731A1

公开(公告)日：2021-09-30

申请号：US17230326

申请日：2021-04-14

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 high pressure compressor section and a low pressure compressor section, the low pressure compressor section including a low pressure compressor section inlet with a low pressure compressor inlet annulus area, a fan duct including a fan duct annulus area outboard of the low pressure compressor section inlet, and a turbine having a high pressure turbine section and a low pressure turbine section driving the fan through a speed reduction mechanism, wherein the low pressure 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：US12129787B2

公开(公告)日：2024-10-29

申请号：US18102356

申请日：2023-01-27

Applicant: Raytheon Technologies Corporation

Inventor： Joseph B. Staubach ,  Joseph E. Turney ,  Neil J. Terwilliger

IPC: F02C3/30

CPC classification number: F02C3/30 ,  F05D2220/323 ,  F05D2240/35

Abstract: A turbine engine assembly an inter-turbine burner that is disposed between at least two of a plurality of turbine stages where an additional amount of fuel is mixed with an exhaust gas flow to generate a reheated gas flow. A condenser extracts water from the reheated gas flow and an evaporator system generates a steam flow from at least a portion of water that is extracted by the condenser for injection into the core airflow.

公开(公告)号：US20240141831A1

公开(公告)日：2024-05-02

申请号：US18311547

申请日：2023-05-03

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Joseph B. Staubach ,  Jon Erik Sobanski

IPC: F02C3/22 ,  F02C3/30 ,  F02C7/141

CPC classification number: F02C3/22 ,  F02C3/30 ,  F02C7/141 ,  F05D2260/211 ,  F05D2260/232

Abstract: A propulsion system for an aircraft includes a core engine generating an exhaust gas flow that is expanded through a turbine section, a hydrogen fuel system suppling hydrogen fuel to the combustor through a fuel flow path, a condenser extracting water from the exhaust gas flow, an evaporator receiving a portion of the water extracted by the condenser and generating a steam flow. The steam flow is injected into a core flow path upstream of the turbine section and a cooled cooling air system uses water extracted from the exhaust gas flow for cooling a cooling airflow communicated to the turbine section.