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公开(公告)号：US20240280050A1
公开(公告)日：2024-08-22
申请号：US18171092
申请日：2023-02-17
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon , William K. Ackermann , Anthony R. Bifulco
CPC classification number: F02C6/08 , F01D9/02 , F05D2220/323 , F05D2240/126 , F05D2260/60
Abstract: A gas turbine engine includes a compressor section having a downstream most location and more upstream locations. A compressor housing surrounds the compressor rotors. A combustor is downstream of the compressor and a turbine section is downstream of the combustor. At least one bleed inlet passage bleeds air compressed from the compressor section, and delivers the air for use on an associated aircraft. A baffle plate is intermediate the at least one bleed inlet passage and a bleed exit port from the gas turbine engine. The baffle plate has a plurality of holes for allowing the air to flow from the bleed inlet passage to the bleed exit port, with an area of the holes increasing from a location adjacent the at least one bleed inlet passage and in a circumferential direction away from the at least one bleed inlet passage. An aircraft air supply system and an aircraft are also disclosed.
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12.发明公开公开(公告)号：US20230167752A1
公开(公告)日：2023-06-01
申请号：US18104375
申请日：2023-02-01
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Frederick M. Schwarz , Gabriel L. Suciu , William K. Ackermann , Daniel Bernard Kupratis , Michael E. McCune
CPC classification number: F01D25/164 , F02K3/06 , F02C3/107 , F01D15/12 , F01D25/162 , F02C7/06 , F02C7/20 , F02C7/36 , F05D2220/32 , F05D2240/60 , F05D2260/40311
Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan, a compressor section, a turbine section including a fan drive turbine and a second turbine, an epicyclic gear system with a gear reduction, first and second bearings, and a fan drive shaft interconnecting the gear system and the fan. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.
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公开(公告)号：US20230021948A1
公开(公告)日：2023-01-26
申请号：US17951370
申请日：2022-09-23
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , William K. Ackermann , Harold W. Hipsky
Abstract: An environmental control system for an aircraft includes a higher pressure tap associated with a higher compression location in a main compressor section. The higher pressure tap leads into a turbine section of a turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive a compressor section of the turbocompressor. A combined outlet receives airflow from a turbine outlet and a compressor outlet intermixing airflow and passing the mixed airflow downstream to be delivered to an aircraft system. A buffer air outlet communicates airflow to an engine buffer air system.
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公开(公告)号：US11560839B2
公开(公告)日：2023-01-24
申请号：US17469025
申请日：2021-09-08
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： William K. Ackermann , Peter M. Munsell
Abstract: A gas turbine engine includes, among other things, a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine, an inner shaft that interconnects the low pressure compressor and the low pressure turbine, an outer shaft that interconnects the high pressure compressor and the high pressure turbine, a bearing structure that supports at least one of the inner and outer shafts, and a buffer system. The buffer system prepares buffer air, communicates the buffer air to the bearing structure to pressurize a bearing compartment, and then from the bearing structure along at least one of the shafts.
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公开(公告)号：US20210396177A1
公开(公告)日：2021-12-23
申请号：US17469025
申请日：2021-09-08
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： William K. Ackermann , Peter M. Munsell
Abstract: A gas turbine engine includes, among other things, a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine, an inner shaft that interconnects the low pressure compressor and the low pressure turbine, an outer shaft that interconnects the high pressure compressor and the high pressure turbine, a bearing structure that supports at least one of the inner and outer shafts, and a buffer system. The buffer system prepares buffer air, communicates the buffer air to the bearing structure to pressurize a bearing compartment, and then from the bearing structure along at least one of the shafts.
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Patent Agency Ranking
公开(公告)号：US11047337B2
公开(公告)日：2021-06-29
申请号：US15485512
申请日：2017-04-12
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Jason Husband , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann
IPC: F02K3/06 , F02C3/107 , F02C7/36 , F02C7/20 , F01D15/12 , F01D5/06 , F04D19/00 , F04D25/04 , F04D29/053 , F04D29/32 , F01D9/04
Abstract: A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with defined flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is between 0.5 and 1.5.
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公开(公告)号：US20230235715A1
公开(公告)日：2023-07-27
申请号：US18130539
申请日：2023-04-04
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Jason Husband , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann
Abstract: A turbofan engine includes a propulsor section that has a propulsor shaft in driving engagement with a propulsor. An epicyclic gear system has a gear mesh lateral stiffness and a gear mesh transverse stiffness. A gear system input defines a gear system input lateral stiffness and a gear system input transverse stiffness. The gear system input lateral stiffness is less than 5% of the gear mesh lateral stiffness. A first turbine section rotates at a first speed, and a second turbine rotates at a second speed that is faster than the first speed. A first performance quantity is defined as the product of the first speed squared and the first area of the first turbine, a second performance quantity is defined as the product of the second speed squared and the second area of the second turbine, and a performance quantity ratio is between 0.5 and 1.5.
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公开(公告)号：US11635043B2
公开(公告)日：2023-04-25
申请号：US17342100
申请日：2021-06-08
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Jason Husband , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann
IPC: F02K3/06 , F02C3/107 , F02C7/36 , F02C7/20 , F01D15/12 , F01D5/06 , F04D19/00 , F04D25/04 , F04D29/053 , F04D29/32 , F01D9/04
Abstract: A turbofan engine includes a fan section that drives air along a bypass flow path in a bypass duct. An epicyclic gear system in driving engagement with the fan shaft and has a gear mesh lateral stiffness and a gear mesh transverse stiffness. A gear system input to the gear system defines a gear system input lateral stiffness and a gear system input transverse stiffness. The gear system input lateral stiffness is less than 5% of the gear mesh lateral stiffness. A first performance quantity is defined as the product of a first speed squared and a first area and a second performance quantity is defined as the product of a second speed squared and a second area. A performance quantity ratio of a first performance quantity to a second performance quantity is between 0.5 and 1.5.
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公开(公告)号：US20210301765A1
公开(公告)日：2021-09-30
申请号：US17342100
申请日：2021-06-08
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Jason Husband , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann
Abstract: A turbofan engine includes a fan section that drives air along a bypass flow path in a bypass duct. An epicyclic gear system in driving engagement with the fan shaft and has a gear mesh lateral stiffness and a gear mesh transverse stiffness. A gear system input to the gear system defines a gear system input lateral stiffness and a gear system input transverse stiffness. The gear system input lateral stiffness is less than 5% of the gear mesh lateral stiffness. A first performance quantity is defined as the product of a first speed squared and a first area and a second performance quantity is defined as the product of a second speed squared and a second area. A performance quantity ratio of a first performance quantity to a second performance quantity is between 0.5 and 1.5.
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公开(公告)号：US10975715B2
公开(公告)日：2021-04-13
申请号：US16123027
申请日：2018-09-06
Applicant: Raytheon Technologies Corporation
Inventor： William K. Ackermann , Clifton J. Crawley, Jr. , Frederick M. Schwarz
Abstract: Assemblies are provided for rotational equipment. One of these assemblies includes a first bladed rotor assembly, a second bladed rotor assembly, a stator vane assembly, a stator structure and a seal assembly. The second bladed rotor assembly includes a rotor disk structure. The stator vane assembly is axially between the first and the second bladed rotor assemblies. The stator structure is mated with and radially within the stator vane assembly. The seal assembly is configured for sealing a gap between the stator structure and the rotor disk structure, wherein the seal assembly includes a non-contact seal.
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