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公开(公告)号：US11459911B2
公开(公告)日：2022-10-04
申请号：US17085153
申请日：2020-10-30
Applicant: Raytheon Technologies Corporation
Inventor： Enzo DiBenedetto
Abstract: A turbine engine strut stage extends through a gaspath upstream of a guide vane stage. A carbon seal system seals a bearing compartment and has: a carbon seal mounted to the case and a seal runner on the spool; and a seal carrier carrying the carbon seal. The engine passes buffer air along a buffer air supply path internally through one or more first struts of the stage of struts. The engine drains oil along an oil drain path internally through one or more second struts of the stage of struts.
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公开(公告)号：US20210317785A1
公开(公告)日：2021-10-14
申请号：US16844683
申请日：2020-04-09
Applicant: Raytheon Technologies Corporation
Inventor： Enzo DiBenedetto , Anthony R. Bifulco , William K. Ackermann , Paul E. Coderre , John H. Mosley , Stephen K. Kramer
Abstract: A cooling system includes an inlet, a passageway, and a feed passage. The inlet is defined by a strut of a diffuser case that extends between a first case portion and a second case portion. The inlet extends from a leading surface towards a trailing surface along a first axis. The passageway is defined by the strut and extends from the inlet towards the second case portion along a second axis that is disposed transverse to the first axis. The feed passage is defined between a body of a tangential onboard injection system that extends between and is connected to an inner vane platform of a guide vane and the second case portion. The feed passage extends along an axis that is disposed parallel to the first axis.
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Patent Agency Ranking
公开(公告)号：US11739661B2
公开(公告)日：2023-08-29
申请号：US17887864
申请日：2022-08-15
Applicant: Raytheon Technologies Corporation
Inventor： Enzo DiBenedetto
CPC classification number: F01D25/183 , F01D9/065 , F02C7/06 , F02C7/28 , F01D25/162 , F05D2220/323 , F05D2240/12 , F05D2240/50 , F05D2240/55 , F05D2260/6022 , F05D2300/224
Abstract: A turbine engine strut stage extends through a gaspath upstream of a guide vane stage. A carbon seal system seals a bearing compartment and has: a carbon seal mounted to the case and a seal runner on the spool; and a seal carrier carrying the carbon seal. The engine passes buffer air along a buffer air supply path internally through one or more first struts of the stage of struts. The engine drains oil along an oil drain path internally through one or more second struts of the stage of struts.
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公开(公告)号：US20220412227A1
公开(公告)日：2022-12-29
申请号：US17887864
申请日：2022-08-15
Applicant: Raytheon Technologies Corporation
Inventor： Enzo DiBenedetto
Abstract: A turbine engine strut stage extends through a gaspath upstream of a guide vane stage. A carbon seal system seals a bearing compartment and has: a carbon seal mounted to the case and a seal runner on the spool; and a seal carrier carrying the carbon seal. The engine passes buffer air along a buffer air supply path internally through one or more first struts of the stage of struts. The engine drains oil along an oil drain path internally through one or more second struts of the stage of struts.
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公开(公告)号：US20220136407A1
公开(公告)日：2022-05-05
申请号：US17085153
申请日：2020-10-30
Applicant: Raytheon Technologies Corporation
Inventor： Enzo DiBenedetto
Abstract: A turbine engine strut stage extends through gaspath upstream of a guide vane stage. A carbon seal system seals a bearing compartment and has: a carbon seal mounted to the case and a seal runner on the spool; and a seal carrier carrying the carbon seal. The engine passes buffer air along a buffer air supply path internally through one or more first struts of the stage of struts. The engine drains oil along an oil drain path internally through one or more second struts of the stage of struts.
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公开(公告)号：US11306604B2
公开(公告)日：2022-04-19
申请号：US16848475
申请日：2020-04-14
Applicant: Raytheon Technologies Corporation
Inventor： Enzo DiBenedetto , Paul E. Coderre
Abstract: A case clearance control system comprising a blade outer air seal support structure having a plurality of protrusions extending radially from the blade outer air seal support structure opposite a blade outer air seal proximate the blade outer air seal support structure; a thermal control ring coupled to the blade outer air seal support structure, the thermal control ring including a plurality of receivers configured to couple with the plurality of protrusions; a thermal break formed between the plurality of protrusions and the plurality of receivers, the thermal break configured to control heat transfer between the blade outer air seal support structure and the thermal control ring; and a plurality of flow passages formed between the blade outer air seal support structure, the thermal control ring and the plurality of protrusions, the plurality of flow passages configured to allow cooling air flow to condition the thermal control ring and maintain thermal control ring dimensions.
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公开(公告)号：US20210317749A1
公开(公告)日：2021-10-14
申请号：US16848475
申请日：2020-04-14
Applicant: Raytheon Technologies Corporation
Inventor： Enzo DiBenedetto , Paul E. Coderre
Abstract: A case clearance control system comprising a blade outer air seal support structure having a plurality of protrusions extending radially from the blade outer air seal support structure opposite a blade outer air seal proximate the blade outer air seal support structure; a thermal control ring coupled to the blade outer air seal support structure, the thermal control ring including a plurality of receivers configured to couple with the plurality of protrusions; a thermal break formed between the plurality of protrusions and the plurality of receivers, the thermal break configured to control heat transfer between the blade outer air seal support structure and the thermal control ring; and a plurality of flow passages formed between the blade outer air seal support structure, the thermal control ring and the plurality of protrusions, the plurality of flow passages configured to allow cooling air flow to condition the thermal control ring and maintain thermal control ring dimensions.
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