公开(公告)号：US20210301730A1

公开(公告)日：2021-09-30

申请号：US17230271

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 ,  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 low pressure compressor section and a high pressure compressor section, the low pressure compressor section including a low pressure compressor section inlet with a low pressure compressor section inlet annulus area, a fan duct including a fan duct annulus area outboard of the a low pressure compressor section inlet, a turbine in fluid communication with the combustor, the turbine having a high pressure turbine section and a low pressure turbine that drives the fan, a speed reduction mechanism coupled to the fan and rotatable by the low pressure turbine section to allow the low pressure turbine section to turn faster than the fan, wherein the low pressure 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 between 0.50 and 0.55, or is greater than 0.55 and less than or equal to 0.65.

公开(公告)号：US20210062725A1

公开(公告)日：2021-03-04

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

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：US20210040898A1

公开(公告)日：2021-02-11

申请号：US16881567

申请日：2020-05-22

Applicant: Raytheon Technologies Corporation

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

IPC: F02C9/18 ,  F02C3/04 ,  F02C7/20 ,  F01D1/02 ,  F01D5/02 ,  F01D9/04 ,  F01D25/24 ,  F02C7/36 ,  F02C3/107 ,  F02K3/06 ,  F02C3/113 ,  F02K3/02 ,  F02K3/075 ,  F02K7/06

Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.

公开(公告)号：US12078084B1

公开(公告)日：2024-09-03

申请号：US18108336

申请日：2023-02-10

Applicant: Raytheon Technologies Corporation

Inventor： Neil J. Terwilliger ,  Joseph B. Staubach

IPC: F01K11/02 ,  F01K7/22 ,  F01K15/02

CPC classification number: F01K11/02 ,  F01K7/223 ,  F01K15/02 ,  F05D2220/72

Abstract: A turbine engine assembly includes a core engine that generates an exhaust gas flow, a condenser where water is extracted from the exhaust gas flow, an evaporator where heat is input into the water that is extracted by the condenser into a first steam flow, a steam turbine where the first steam flow is expanded and cooled, and a superheater where additional heat is input into the first steam flow that is exhausted from the steam turbine to generate a second steam flow. The second steam flow is injected into a core flow path of the core engine.

公开(公告)号：US20240151179A1

公开(公告)日：2024-05-09

申请号：US17980957

申请日：2022-11-04

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Steven W. Burd ,  Joseph B. Staubach ,  David Lei Ma

IPC: F02C3/107 ,  F02C7/32

CPC classification number: F02C3/107 ,  F02C7/32 ,  F05D2220/323 ,  F05D2220/60 ,  F05D2240/35 ,  F05D2260/4031

Abstract: An aircraft power system includes an internal combustion core engine where an inlet airflow is mixed with a fuel and ignited to generate shaft power and a primary gas flow, a boost combustor where a portion of the primary gas flow from the core engine is combined with fuel and ignited to generate a boosted gas flow, and a drive turbine that includes a drive output shaft wherein the boosted gas flow is expanded to generate shaft power.

公开(公告)号：US20240141837A1

公开(公告)日：2024-05-02

申请号：US18311460

申请日：2023-05-03

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jesse M Chandler ,  Marc J. Muldoon ,  Jon E. Sobanski ,  Neil J. Terwilliger ,  Joseph B. Staubach

IPC: F02C7/22 ,  F02C7/18

CPC classification number: F02C7/22 ,  F02C7/18 ,  F05D2260/211

Abstract: A propulsion system for an aircraft includes a gas generating core engine generates an exhaust gas flow that is expanded through a turbine section, a power turbine driven by the exhaust gas flow, a propulsor coupled to the power turbine, a hydrogen fuel system configured to supply hydrogen fuel to the combustor through a fuel flow path, a condenser arranged along the core flow path and configured to extract water from the exhaust gas flow, and an evaporator arranged along the core flow path receiving a portion of the water extracted by the condenser to generate a steam flow that is injected into the core flow path upstream of the turbine section.

公开(公告)号：US20240102416A1

公开(公告)日：2024-03-28

申请号：US17951879

申请日：2022-09-23

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： David Lei Ma ,  Joseph B. Staubach

IPC: F02C3/30

CPC classification number: F02C3/30 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2270/08

Abstract: A turbine engine assembly includes a turbine section including at plurality of turbine stages through which the gas flow expands to generate a mechanical power output. An inter-turbine burner between at least two of the plurality of turbine stages reheats the gas flow. A condenser extracts water from the gas flow exhausted from the turbine section, and an evaporator heats the water extracted by the condenser to generate a steam flow with the steam flow communicated to the inter-turbine burner and added to the gas flow expanded through the turbine section.

公开(公告)号：US20230374938A1

公开(公告)日：2023-11-23

申请号：US18314384

申请日：2023-05-09

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Joseph B. Staubach ,  Jon Erik Sobanski

IPC: F02C3/22 ,  F02C7/141 ,  F02C6/20

CPC classification number: F02C3/22 ,  F02C7/141 ,  F02C6/20 ,  B64D27/10

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. A propulsor is coupled to the power turbine. A hydrogen fuel system supplies hydrogen fuel to the combustor through a fuel flow path. A condenser extracts water from the exhaust gas flow. 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. An inlet duct communicates an inlet airflow to the compressor section aft at a location aft of the turbine section. An exhaust duct routes exhaust gas flow through the condenser and into thermal communication with a water flow of water extracted in the condenser in the evaporator.

公开(公告)号：US11802508B2

公开(公告)日：2023-10-31

申请号：US17708095

申请日：2022-03-30

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Lance L. Smith ,  David Lei Ma ,  Joseph B. Staubach ,  Brian M. Holley ,  Sean C. Emerson

IPC: F02C3/22 ,  F02C7/224 ,  F02C3/04 ,  F23R3/30 ,  F02C3/24 ,  C01B3/04

CPC classification number: F02C3/22 ,  F02C3/04 ,  F02C7/224 ,  F23R3/30 ,  C01B3/047 ,  F02C3/24

Abstract: A gas turbine engine includes a core engine that includes a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with an ammonia based fuel and ignited to generate a high energy combusted gas flow that is expanded through a turbine section. The turbine section is mechanically coupled to drive the compressor section. An ammonia flow path communicates an ammonia flow to the combustor section. A cracking device is disposed in the ammonia flow path. The cracking device is configured to decompose the ammonia flow into a fuel flow containing hydrogen (H2). At least one heat exchanger is upstream of the cracking device that provides thermal communication between the ammonia flow and a working fluid flow such that the ammonia fluid flow accepts thermal energy from the working fluid flow.

公开(公告)号：US11781478B2

公开(公告)日：2023-10-10

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: F02K3/12 ,  F02C6/20 ,  F02C7/36

CPC classification number: F02C6/20 ,  F02C7/36 ,  F02K3/12

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.