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公开(公告)号：US10746038B2
公开(公告)日：2020-08-18
申请号：US15354054
申请日：2016-11-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Tracey A. Propheter-Hinckley , Michael G. McCaffrey
IPC: F01D11/02 , F01D11/00 , F01D17/16 , F01D5/14 , F01D9/04 , F01D5/18 , F01D5/28 , F01D5/12 , F01D9/02 , F02C3/04 , F04D29/08 , F04D29/32 , F04D29/54 , F01D5/30
Abstract: An airfoil includes an airfoil piece that defines at least a portion of an airfoil profile. The airfoil piece has a radial end and a first radial slot in the radial end. An end section has a second radial slot adjacent the first radial slot. The first radial slot and the second radial slot together form a radial seal slot. A seal is disposed in the radial seal slot.
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公开(公告)号：US10738643B2
公开(公告)日：2020-08-11
申请号：US16164958
申请日：2018-10-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey , Benjamin F. Hagan , David Richard Griffin
Abstract: A seal assembly includes a seal arc segment defining first and second seal supports with a carriage defining first and second support members. The first support member supports the seal arc segment in a first ramped interface, and the second support member supports the seal arc segment in a second ramped interface. A spring is configured to bias the seal arc segment axially. A heat shield is radially inward of the spring.
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公开(公告)号：US10677079B2
公开(公告)日：2020-06-09
申请号：US15354093
申请日：2016-11-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Abstract: An airfoil includes an airfoil section that has radially inner and outer ends and defines an airfoil profile. The airfoil profile has a leading end, a trailing end, a suction side, and a pressure side. The airfoil section includes a ceramic airfoil piece that defines a portion of the airfoil profile. The ceramic airfoil piece includes an exterior wall that has an internal cooling circuit.
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公开(公告)号：US10648668B2
公开(公告)日：2020-05-12
申请号：US14904608
申请日：2014-06-18
Applicant: United Technologies Corporation
Inventor： Grant O. Cook, III , Michael G. Abbott , Michael G. McCaffrey
Abstract: A gas turbine engine component assembly includes a ceramic component having a first thermal characteristic. A metallic component has a second thermal characteristic. A bonding material secures the ceramic component to the metallic component. The bonding material includes at least one of a transient liquid phase bond and a partial transient liquid phase bond. The bonding material is configured to withstand a shear stress parameter relating to a differential between the first and second thermal characteristics.
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公开(公告)号：US10598046B2
公开(公告)日：2020-03-24
申请号：US16032656
申请日：2018-07-11
Applicant: United Technologies Corporation
Inventor： Michael G. McCaffrey , Scott D. Virkler
Abstract: A method of assembling a portion of a gas turbine engine, includes assembling a plurality of static structure rings; attaching a plurality of support straps to an outer diameter of the plurality of static structure rings to form a cartridge; inserting the cartridge at least partially into an outer case assembly along an engine axis.
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Patent Agency Ranking
公开(公告)号：US20200018189A1
公开(公告)日：2020-01-16
申请号：US16032656
申请日：2018-07-11
Applicant: United Technologies Corporation
Inventor： Michael G. McCaffrey , Scott D. Virkler
Abstract: A method of assembling a portion of a gas turbine engine, includes assembling a plurality of static structure rings; attaching a plurality of support straps to an outer diameter of the plurality of static structure rings to form a cartridge; inserting the cartridge at least partially into an outer case assembly along an engine axis.
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公开(公告)号：US10458249B2
公开(公告)日：2019-10-29
申请号：US15033933
申请日：2014-11-05
Applicant: United Technologies Corporation
Inventor： Michael G. McCaffrey , Ioannis Alvanos , Michael G. Abbott , Grant O. Cook, III
Abstract: An airfoil component includes a first segment that has a first piece of a mount and a first piece of an airfoil. The first segment is formed of a first ceramic-based material. A second segment includes a second piece of the mount and a second piece of the airfoil. The second segment is formed of a second ceramic-based material. The first and second segments are bonded together along a bond joint such that the first and second pieces of the mount are bonded to each other and the first and second pieces of the airfoil are bonded to each other.
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公开(公告)号：US10436070B2
公开(公告)日：2019-10-08
申请号：US15021052
申请日：2014-08-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey
Abstract: A blade outer air seal (BOAS) according to an exemplary aspect of the present disclosure includes, among other things, a ceramic body having a radially inner face and a radially outer face and a retention feature that extends from the radially outer face. The retention feature includes at least one angled hook that extends at a transverse angle relative to the radially outer face.
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公开(公告)号：US10422240B2
公开(公告)日：2019-09-24
申请号：US15071299
申请日：2016-03-16
Applicant: United Technologies Corporation
Inventor： Michael G. McCaffrey
Abstract: A seal assembly includes a seal arc segment that defines radially inner and outer sides and first and second axial arc segment sides, a carriage that carries the seal arc segment, and a cover that defines first and second axial cover sides. The second axial cover side is adjacent the first axial arc segment side.
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公开(公告)号：US10415419B2
公开(公告)日：2019-09-17
申请号：US15406324
申请日：2017-01-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Fanping Sun , Zaffir A. Chaudhry , Lee A. Hoffman , Hailing Wu , Seung Bum Kim , Michael G. McCaffrey , Joel H. Wagner
Abstract: A system for modulating turbine blade tip clearance is provided. The system may comprise an actuation control system having at least one actuator configured to modulate turbine blade tip clearance between a turbine blade tip and a blade outer air seal (BOAS). Each actuator may be coupled to the BOAS. Each actuator may comprise a solid-state motion amplification device such as a flextensional actuator. The actuators may be configured to move the BOAS in a radial direction from a first position to a second position to control tip clearance.
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