公开(公告)号：US20210246828A1

公开(公告)日：2021-08-12

申请号：US16785853

申请日：2020-02-10

Applicant: United Technologies Corporation

Inventor： Nigel David Sawyers-Abbott ,  Kenneth N. Baker, Ph.D.

IPC: F02C7/06 ,  F01D25/20

Abstract: A lubrication system for a gas turbine engine includes a primary fluid tank to receive a primary fluid, at least one secondary fluid tank to receive at least one fluid additive, and a mixer. The mixer has at least a first inlet in fluid communication with the primary fluid tank and a second inlet in fluid communication with the at least one secondary fluid tank. The mixer has at least one outlet that delivers a mixture of the primary fluid and the at least one fluid additive to a gas turbine engine component.

公开(公告)号：US20210003485A1

公开(公告)日：2021-01-07

申请号：US16502242

申请日：2019-07-03

Applicant: United Technologies Corporation

Inventor： Joel H. Wagner ,  Kevin W. Schlichting ,  Michael Joseph Murphy ,  Steven H. Zysman ,  Nigel David Sawyers-Abbott ,  Andrew A. Consiglio ,  Charles Waldo Haldeman, IV

IPC: G01N1/22 ,  G01N23/223

Abstract: An environmental sampling system includes a passage in an aircraft component and a removable collector disposed in the passage. The passage has an inlet at a first region and an outlet at a second region. When the aircraft component is in operation the first region is at a greater pressure than the second region such that air flows through the passage from the inlet to the outlet. The removable collector is configured to retain constituents from the air and to react with the media designed to mimic corrosion effects seen at higher temperatures on engine parts. The constituents can then be characterized and correlated to engine deterioration to predict maintenance activity.

公开(公告)号：US20200300171A1

公开(公告)日：2020-09-24

申请号：US16358760

申请日：2019-03-20

Applicant: United Technologies Corporation

Inventor： Nigel David Sawyers-Abbott ,  Federico Papa

IPC: F02C7/25 ,  A62C3/08 ,  B64C7/02 ,  F02C9/18 ,  F02K3/04 ,  F02C9/34

Abstract: A gas turbine engine includes an engine core having a compressor, a combustor fluidly connected to the compressor, and a turbine fluidly connected to the combustor. A core nacelle is disposed radially outward of the engine core. A cavity is disposed between an inner surface of the core nacelle and an outer surface of the engine core. The cavity includes a vent disposed at an aft end. The vent includes at least one flap configured to be maintained in an unrestricted position and in a restricted position. An actuator is configured to control the position of the at least one flap.

公开(公告)号：US10648427B2

公开(公告)日：2020-05-12

申请号：US14970214

申请日：2015-12-15

Applicant: United Technologies Corporation

Inventor： Nigel David Sawyers-Abbott ,  James Power

IPC: F02K1/72 ,  F02K1/76

Abstract: The present disclosure relates generally to a thrust reverser for a gas turbine engine. As a translating cowl is translated aft from the nacelle of the gas turbine engine, a cascade is also translated in the aft direction and a blocker door coupled to the cascade is pivoted into a fan duct by means of a camming surface, thereby diverting air in the fan duct through the cascade. In the stowed position, both the cascade and the blocker door are disposed radially outward of a radially inner wall of the nacelle and/or the translating cowl.

公开(公告)号：US10605197B2

公开(公告)日：2020-03-31

申请号：US14955919

申请日：2015-12-01

Applicant: United Technologies Corporation

Inventor： Nigel David Sawyers-Abbott ,  James Power

IPC: F02K1/72

Abstract: The present disclosure relates generally to a thrust reverser for a gas turbine engine. As a translating cowl is translated aft from the nacelle of the gas turbine engine, a cascade is also translated in the aft direction and a blocker door coupled to the cascade is pivoted into a fan duct, thereby diverting air in the fan duct through the cascade. In the stowed position, both the cascade and the blocker door are disposed radially outward of a radially inner wall of the nacelle and/or the translating cowl.

公开(公告)号：US10400621B2

公开(公告)日：2019-09-03

申请号：US14765037

申请日：2014-02-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Nigel David Sawyers-Abbott ,  Constantino V. Loffredo

IPC: F02K1/09 ,  F02K1/70 ,  F02K1/72 ,  F01D17/14 ,  F02K1/12 ,  F01D9/04 ,  F01D25/24 ,  F02K1/15 ,  F02K1/76 ,  F02K3/075

Abstract: A gas turbine engine includes a nacelle assembly having a core nacelle defined about an engine axis and a fan nacelle assembly mounted at least partially around the core nacelle to define a fan bypass flow path. The fan nacelle assembly includes a fan duct nacelle section and a fan nozzle nacelle section moveable relative to the fan duct nacelle section. A thrust reverser system includes a plurality of pivot doors movable relative to the fan nacelle assembly between stowed and deployed positions. A variable area fan nozzle is in communication with the fan bypass flow path. A first actuator is mounted to the fan duct nacelle section to actuate the pivot door thrust reverser system, and a second actuator is mounted to the fan duct nacelle section to move the fan nozzle nacelle section relative to the fan duct nacelle section to vary a fan nozzle exit area.

公开(公告)号：US10370111B2

公开(公告)日：2019-08-06

申请号：US15258927

申请日：2016-09-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Nigel David Sawyers-Abbott ,  Matthew Exner

IPC: B64D29/06 ,  B64D27/16 ,  F01D25/24 ,  F02K1/56 ,  F02K1/76 ,  F02K1/72 ,  F16C11/04

Abstract: A linkage system for a nacelle may comprise a pivot configured to extend through a second aperture disposed in a link arm, a base member, and a retaining member at least partially defining a first aperture and a cavity. The pivot is configured to extend at least partially into the first aperture. The cavity is configured to accommodate a portion of the link arm.

公开(公告)号：US20190085789A1

公开(公告)日：2019-03-21

申请号：US15711229

申请日：2017-09-21

Applicant: United Technologies Corporation

Inventor： Andre L. Bent ,  Steven H. Zysman ,  Nigel David Sawyers-Abbott

IPC: F02K1/56 ,  F02C9/18 ,  F02K1/06 ,  F02K1/32

Abstract: An exhaust section of a gas turbine engine includes an exhaust plug defining a plurality of exhaust plug apertures circumferentially spaced from each other. Also included is an exhaust nozzle radially offset from the exhaust plug defining an exhaust pathway between the exhaust plug and the exhaust nozzle. Further included is an exhaust plug liner having a non-uniform outer surface axially aligned with the exhaust plug apertures. The exhaust plug liner is rotatable relative to exhaust plug between a first position and a second position to selectively change a cross-sectional area of the exhaust pathway during thrust reversal operation to increase an amount of reverse thrust.

公开(公告)号：US20180355821A1

公开(公告)日：2018-12-13

申请号：US15619029

申请日：2017-06-09

Applicant: United Technologies Corporation

Inventor： Andre L. Bent ,  Steven H. Zysman ,  Nigel David Sawyers-Abbott

IPC: F02K1/70 ,  F02K3/06 ,  F02C3/04

CPC classification number: F02K1/70 ,  F02C3/04 ,  F02K1/08 ,  F02K1/16 ,  F02K1/72 ,  F02K3/06 ,  F05D2260/57 ,  F05D2270/62 ,  F05D2270/65

Abstract: An exhaust section of a gas turbine engine includes an exhaust plug, and an exhaust nozzle radially offset from the exhaust plug defining an exhaust pathway between the exhaust plug and the exhaust nozzle. The exhaust plug is configured for axial translation relative to exhaust nozzle between a first position and a second position to selectably change a cross-sectional area of the exhaust pathway during thrust reversal operation of the gas turbine engine to reduce an amount of reverse thrust necessary. A method of operating a gas turbine engine includes actuating a fan thrust reverser to divert a fan airflow from a fan airflow pathway, and translating an exhaust plug from a first position to a second position, thereby increasing a cross-sectional area of an exhaust pathway to reduce an amount of reverse thrust necessary.

公开(公告)号：US10060292B2

公开(公告)日：2018-08-28

申请号：US14774168

申请日：2014-03-13

Applicant: United Technologies Corporation

Inventor： Nigel David Sawyers-Abbott

IPC: B64D29/08 ,  F01D25/26 ,  B64D29/06 ,  F01D25/28 ,  F02K1/72 ,  F02C7/20 ,  F01D25/24 ,  F01D15/10 ,  F02C3/04 ,  F02K1/80

CPC classification number: F01D25/265 ,  B64D29/06 ,  B64D29/08 ,  F01D15/10 ,  F01D25/246 ,  F01D25/28 ,  F02C3/04 ,  F02C7/20 ,  F02K1/72 ,  F02K1/80 ,  F02K1/805 ,  F05D2220/32 ,  F05D2250/182 ,  F05D2250/71 ,  F05D2260/36

Abstract: A gas turbine engine includes a fan duct including a fan duct inner structure that surrounds a core engine, a fan case that surrounds a fan, a core engine frame, and at least one mechanism configured to secure a portion of the fan duct inner structure to a portion of the core engine frame. The at least one mechanism includes a castellated arcuate portion mounted to one of the fan duct inner structure and the core engine frame and an inwardly projecting retaining feature mounted to the other of the fan duct inner structure and the core engine frame. The castellated arcuate portion is rotatable about an engine central longitudinal axis to position a feature of the castellated arcuate portion proximate to a portion of the inwardly projecting retaining feature to latch the fan duct inner structure.