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公开(公告)号：US09828876B2
公开(公告)日：2017-11-28
申请号：US14696963
申请日：2015-04-27
Applicant: Rolls-Royce Corporation
Inventor： Matthew J. Kappes
CPC classification number: F01D25/24 , F01D11/122 , F01D21/045 , F01D25/04 , F05D2220/32 , F05D2220/36 , F05D2230/50 , F05D2230/60 , F05D2300/6012 , F05D2300/603 , F05D2300/615 , Y02T50/672
Abstract: A fan case for use in a gas turbine engine of an aircraft includes an outer shroud and a liner extending along the outer shroud. The fan case provides a protective band that blocks fan blades from being thrown out of the fan case in case of a blade-off event in which a fan blade is released during operation of the gas turbine engine.
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公开(公告)号：US20160069214A1
公开(公告)日：2016-03-10
申请号：US14839113
申请日：2015-08-28
Inventor： Eric W. Engebretsen , Daniel E. Molnar, JR. , Matthew J. Kappes
IPC: F01D25/24
Abstract: A fan case for use in a gas turbine engine of an aircraft includes an outer shroud and a liner extending along the outer shroud. The fan case provides a protective band that blocks fan blades from being thrown out of the fan case in case of a blade-off event in which a fan blade is released during operation of the gas turbine engine.
Abstract translation: 用于飞行器的燃气涡轮发动机的风扇壳体包括外护罩和沿外护罩延伸的衬套。 风扇壳提供了一个保护带，其阻止风扇叶片在燃气涡轮发动机运行期间风扇叶片被释放的叶片关闭事件的情况下被丢出风扇壳体。
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公开(公告)号：US20210355833A1
公开(公告)日：2021-11-18
申请号：US15930158
申请日：2020-05-12
Applicant: Rolls-Royce Corporation
Inventor： Robert Heeter , Matthew J. Kappes , Jonathan Michael Rivers , Benedict N. Hodgson
Abstract: A composite aerofoil may include an aerofoil body defining a leading edge and a trailing edge, wherein the body comprises a composite material including a plurality of relatively higher-modulus reinforcement elements, a plurality of relatively tougher polymer-based reinforcement elements, and a matrix material substantially encapsulating the plurality of relatively higher-modulus reinforcement elements and the plurality of relatively tougher polymer-based reinforcement elements. The plurality of relatively higher-modulus reinforcement elements are different from the plurality of relatively tougher polymer-based reinforcement elements. The disclosure also describes techniques for forming composite aerofoils.
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公开(公告)号：US20180112557A1
公开(公告)日：2018-04-26
申请号：US15299022
申请日：2016-10-20
Applicant: Rolls-Royce Corporation
Inventor： Matthew J. Kappes , Erin M. Romanowski , Dennes K. Burney
CPC classification number: F01D25/243 , F01D21/045 , F01D25/005 , F05D2220/32 , F05D2260/31
Abstract: According to one aspect, a flange fastening assembly for a gas turbine engine includes a first flange having a first hole therein, a second flange having a second hole disposed adjacent to the first flange, and a shoulder bolt disposed through the first hole and the second hole. The shoulder bolt has a head portion, a stem portion, and a thread portion, and the stem portion and the thread portion define a shoulder. A bolt nut is disposed on the thread portion and a first spacer is disposed between the bolt nut and the first flange such that the first spacer overhangs the shoulder.
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公开(公告)号：US20180066675A1
公开(公告)日：2018-03-08
申请号：US15257206
申请日：2016-09-06
Applicant: Rolls-Royce Corporation
Inventor： Matthew J. Kappes , Robert W. Heeter , Benedict N. Hodgson
CPC classification number: F04D29/526 , F01D21/04 , F02K3/06 , F04D19/002 , F04D29/164 , F04D29/324 , F05D2220/32 , F05D2300/224 , F05D2300/603 , Y02T50/672
Abstract: According to one aspect, a fan containment case for a gas turbine engine is provided which includes a barrel having a first band of material on an outside of the barrel. The first band is made of carbon fiber composite. The barrel further includes a second band of material inboard of the fan case and made of poly p-phenylene-2,6-benzobisoxazole (PBO) composite. The barrel also includes a third band of material made of carbon fiber composite inboard of the second band.
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Patent Agency Ranking
公开(公告)号：US20150308290A1
公开(公告)日：2015-10-29
申请号：US14696963
申请日：2015-04-27
Applicant: Rolls-Royce Corporation
Inventor： Matthew J. Kappes
CPC classification number: F01D25/24 , F01D11/122 , F01D21/045 , F01D25/04 , F05D2220/32 , F05D2220/36 , F05D2230/50 , F05D2230/60 , F05D2300/6012 , F05D2300/603 , F05D2300/615 , Y02T50/672
Abstract: A fan case for use in a gas turbine engine of an aircraft includes an outer shroud and a liner extending along the outer shroud. The fan case provides a protective band that blocks fan blades from being thrown out of the fan case in case of a blade-off event in which a fan blade is released during operation of the gas turbine engine.
Abstract translation: 用于飞行器的燃气涡轮发动机的风扇壳体包括外护罩和沿外护罩延伸的衬套。 风扇壳提供了一个保护带，其阻止风扇叶片在燃气涡轮发动机运行期间风扇叶片被释放的叶片关闭事件的情况下被丢出风扇壳体。
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公开(公告)号：US11193375B2
公开(公告)日：2021-12-07
申请号：US16674745
申请日：2019-11-05
Applicant: Rolls-Royce Corporation
Inventor： Patrick E. Bailey , Samuel J. Lacombe , Eric W. Engebretsen , Rodney D. Conrad , Matthew J. Kappes
IPC: F01D5/06
Abstract: A fan assembly for use in a gas turbine engine of an aircraft includes a fan disk having a number of fan blades and a windage shield coupled to the fan disk to move therewith. The fan assembly supplies air for use in the engine. The windage shield rotates with the fan disk during operation of the gas turbine engine and directs air supplied by the fan blade.
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公开(公告)号：US10746031B2
公开(公告)日：2020-08-18
申请号：US16037980
申请日：2018-07-17
Applicant: Rolls-Royce Corporation
Inventor： Robert Heeter , Matthew J. Kappes
Abstract: An annulus filler may include an outer lid defining an airflow surface for air being drawn through the engine in an axial airflow direction and a support structure configured to connect the outer lid to a rotor disc. The annulus filler may include a composite material including a plurality of relatively high-modulus reinforcement elements, a plurality of relatively tough polymer-based reinforcement elements, and a matrix material substantially encapsulating the plurality of relatively high-modulus reinforcement elements and the plurality of relatively tough reinforcement elements.
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公开(公告)号：US20200063563A1
公开(公告)日：2020-02-27
申请号：US16674745
申请日：2019-11-05
Applicant: Rolls-Royce Corporation
Inventor： Patrick E. Bailey , Samuel J. Lacombe , Eric W. Engebretsen , Rodney D. Conrad , Matthew J. Kappes
IPC: F01D5/06
Abstract: A fan assembly for use in a gas turbine engine of an aircraft includes a fan disk having a number of fan blades and a windage shield coupled to the fan disk to move therewith. The fan assembly supplies air for use in the engine. The windage shield rotates with the fan disk during operation of the gas turbine engine and directs air supplied by the fan blade.
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公开(公告)号：US20190112934A1
公开(公告)日：2019-04-18
申请号：US16037980
申请日：2018-07-17
Applicant: Rolls-Royce Corporation
Inventor： Robert Heeter , Matthew J. Kappes
IPC: F01D5/30
CPC classification number: F01D5/30 , F01D11/008 , F05D2220/32 , F05D2220/36 , F05D2230/20 , F05D2230/21 , F05D2230/41 , F05D2230/90 , F05D2240/30 , F05D2300/2102 , F05D2300/224 , F05D2300/43 , F05D2300/433 , F05D2300/6012 , F05D2300/603
Abstract: An annulus filler may include an outer lid defining an airflow surface for air being drawn through the engine in an axial airflow direction and a support structure configured to connect the outer lid to a rotor disc. The annulus filler may include a composite material including a plurality of relatively high-modulus reinforcement elements, a plurality of relatively tough polymer-based reinforcement elements, and a matrix material substantially encapsulating the plurality of relatively high-modulus reinforcement elements and the plurality of relatively tough reinforcement elements.
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