公开(公告)号：US20230249837A1

公开(公告)日：2023-08-10

申请号：US17650318

申请日：2022-02-08

Applicant: Gulfstream Aerospace Corporation

Inventor： Donald Freund ,  Derek Muzychka ,  Douglas Klutzke

IPC: F01D25/24 ,  B64D27/26 ,  B64D27/02 ,  B64D29/06

CPC classification number: F01D25/24 ,  B64D27/26 ,  B64D27/02 ,  B64D29/06

Abstract: An inlet arrangement for a propulsion system includes an actuator, a linkage and an inlet assembly. The inlet assembly includes (1) a lip, (2) a cowl extending downstream from the lip, the cowl defining an external surface of the inlet assembly, (3) an inlet duct extending downstream from the lip, the inlet duct disposed radially inward of the cowl, and (4) a movable component associated with the lip, the cowl, or the inlet duct. An outer surface of the inlet duct and an inner surface of the cowl define a gap therebetween. The linkage is disposed in the gap and coupled with the moveable component. The linkage is configured to move within the gap and to move the moveable component when the linkage moves. The actuator is coupled with the linkage and moves the linkage when the actuator is actuated. The actuator is mounted remotely from the inlet assembly.

公开(公告)号：US11686246B2

公开(公告)日：2023-06-27

申请号：US17451137

申请日：2021-10-15

Applicant: Gulfstream Aerospace Corporation

Inventor： Shawn Bennett ,  Joe Gavin ,  Nicholas Powell ,  Donald Freund ,  Derek Muzychka ,  John Louis

IPC: F02C7/042 ,  F02C7/057 ,  F02K1/16 ,  B64D33/02

CPC classification number: F02C7/042 ,  F02C7/057 ,  F02K1/165 ,  B64D2033/0206 ,  B64D2033/026 ,  B64D2033/0226 ,  F05D2220/323 ,  F05D2270/122

Abstract: An aircraft propulsion system includes an engine. The propulsion system further includes an inlet having a forward cowl lip and an aft cowl lip. The forward cowl lip moves between retracted and deployed positions. The forward cowl lip is adjacent to the aft cowl lip when retracted. The forward cowl lip is spaced apart from the aft cowl lip when deployed. The forward cowl lip has a smaller radius of curvature than the aft cowl lip. The propulsion system further includes a controller coupled with the engine and inlet. The controller restricts the maximum thrust commanded position of the engine when the aircraft is on the ground and moving below a predetermined speed. The controller lifts the restriction when the aircraft is moving at at least the predetermined speed. The controller controls the inlet to deploy the cowl lip when the aircraft is on the ground.

公开(公告)号：US20240280065A1

公开(公告)日：2024-08-22

申请号：US18646133

申请日：2024-04-25

Applicant: Gulfstream Aerospace Corporation

Inventor： Derek Muzychka ,  Donald Freund ,  Andrew Clemens ,  John Louis ,  Joseph Gavin ,  Till Gerhardt ,  William Mcfarland ,  Benjamin Walke

IPC: F02K1/76 ,  B64C7/02 ,  F02K1/72

CPC classification number: F02K1/763 ,  B64C7/02 ,  F02K1/72 ,  F05D2220/323

Abstract: Various non-limiting embodiments of a nozzle assembly for use with a propulsion system and a sleeve assembly for use with the nozzle assembly are disclosed herein. In a non-limiting embodiment, the nozzle assembly includes, but is not limited to, a nacelle. The nozzle assembly further includes, but is not limited to, a sleeve assembly mounted within the nacelle downstream of the engine. The sleeve assembly is configured to receive the mass flow from the engine and to guide the mass flow to an exit of the propulsion system. The sleeve assembly is comprised of a plurality of sleeve segments arranged in a circumferential configuration. Each sleeve segment of the plurality of sleeve segments has an elongate body that is longitudinally aligned with a longitudinal axis of the sleeve assembly.

公开(公告)号：US20240059421A1

公开(公告)日：2024-02-22

申请号：US18494181

申请日：2023-10-25

Applicant: Gulfstream Aerospace Corporation

Inventor： Donald Freund ,  Derek Muzychka

IPC: B64D33/04 ,  B64D27/16 ,  B64D29/02 ,  B64D29/04 ,  B64D29/06 ,  F02K1/56 ,  F02K1/76

CPC classification number: B64D33/04 ,  B64D27/16 ,  B64D29/02 ,  B64D29/04 ,  B64D29/06 ,  F02K1/56 ,  F02K1/763

Abstract: An exhaust nozzle assembly includes, but is not limited to, a nozzle body configured to be fluidly coupled with an engine and to receive a jet produced by the engine. An outer cover covers the nozzle body. A movable component is disposed and configured to have an effect on either the jet or an exhaust plume when the movable component moves. A linkage is coupled to the movable component and adapted for coupling to an actuator. The linkage transmits the force to the moveable component from the actuator. There is a gap between an inner surface of the outer cover and an outer surface of the nozzle body. The linkage is smaller than the actuator. The gap is smaller than a smallest dimension of the actuator and larger than the linkage. The linkage is partially disposed within the gap, and the exhaust nozzle assembly is free of the actuator.

公开(公告)号：US20220009645A1

公开(公告)日：2022-01-13

申请号：US17302325

申请日：2021-04-30

Applicant: Gulfstream Aerospace Corporation

Inventor： Donald Freund ,  Derek Muzychka ,  Douglas Klutzke

IPC: B64D27/26 ,  B64D29/04 ,  B64D29/02 ,  B64D27/18 ,  B64D27/20

Abstract: A propulsion system for an aircraft is taught herein. The propulsion system includes, but is not limited to, an engine. The propulsion system further includes, but is not limited to, an outer cover associated with the engine. The engine and the outer cover are configured for coupling to the aircraft. The propulsion system further includes, but is not limited to, an external engine component. The propulsion system still further includes, but is not limited to, a coupler that operatively couples the external engine component to the engine. The external engine component is configured to be coupled to the aircraft at a location spaced apart from the engine.

公开(公告)号：US12280888B2

公开(公告)日：2025-04-22

申请号：US18494181

申请日：2023-10-25

Applicant: Gulfstream Aerospace Corporation

Inventor： Donald Freund ,  Derek Muzychka

IPC: B64D33/04 ,  B64D27/16 ,  B64D29/02 ,  B64D29/04 ,  B64D29/06 ,  F02K1/56 ,  F02K1/76

Abstract: An exhaust nozzle assembly includes, but is not limited to, a nozzle body configured to be fluidly coupled with an engine and to receive a jet produced by the engine. An outer cover covers the nozzle body. A movable component is disposed and configured to have an effect on either the jet or an exhaust plume when the movable component moves. A linkage is coupled to the movable component and adapted for coupling to an actuator. The linkage transmits the force to the moveable component from the actuator. There is a gap between an inner surface of the outer cover and an outer surface of the nozzle body. The linkage is smaller than the actuator. The gap is smaller than a smallest dimension of the actuator and larger than the linkage. The linkage is partially disposed within the gap, and the exhaust nozzle assembly is free of the actuator.

公开(公告)号：US12264638B2

公开(公告)日：2025-04-01

申请号：US18307162

申请日：2023-04-26

Applicant: Gulfstream Aerospace Corporation

Inventor： Derek Muzychka ,  Donald Freund ,  Andrew Clemens ,  John Louis ,  Joseph Gavin ,  Till Gerhardt ,  William Mcfarland ,  Benjamin Walke

IPC: F02K1/09 ,  B64C7/02 ,  F02K1/72 ,  F02K1/76 ,  G06F1/16 ,  G06V40/12 ,  G06V40/13

Abstract: A nozzle assembly includes a sleeve defining a pathway, the sleeve disposed within a nacelle. The pathway and an internal surface of the nacelle guides a mass flow from an engine to an exit of the propulsion system. The sleeve is configured to move between a forward position an aft position within the nacelle aft of the engine. The sleeve has a protruding portion that extends towards a center of the pathway and that defines a smallest internal diameter of the sleeve. The sleeve includes a plurality of sleeve segments that are longitudinally aligned and circumferentially arranged to form the sleeve. The sleeve segments are configured to move circumferentially closer as the sleeve moves in a first direction within the nacelle and to move circumferentially further apart as the sleeve moves in a second direction within the nacelle. An actuator is coupled with, and is configured to move the sleeve.

公开(公告)号：US11834189B2

公开(公告)日：2023-12-05

申请号：US17301239

申请日：2021-03-30

Applicant: Gulfstream Aerospace Corporation

Inventor： Donald Freund ,  Derek Muzychka

IPC: B64D33/04 ,  B64D27/16 ,  B64D29/02 ,  B64D29/04 ,  B64D29/06 ,  F02K1/56 ,  F02K1/76

CPC classification number: B64D33/04 ,  B64D27/16 ,  B64D29/02 ,  B64D29/04 ,  B64D29/06 ,  F02K1/56 ,  F02K1/763

Abstract: An exhaust nozzle assembly includes, but is not limited to, a nozzle body configured to be fluidly coupled with an engine and to receive a jet produced by the engine. An outer cover covers the nozzle body. A movable component is disposed and configured to have an effect on either the jet or an exhaust plume when the movable component moves. A linkage is coupled to the movable component and adapted for coupling to an actuator. The linkage transmits the force to the moveable component from the actuator. There is a gap between an inner surface of the outer cover and an outer surface of the nozzle body. The linkage is smaller than the actuator. The gap is smaller than a smallest dimension of the actuator and larger than the linkage. The linkage is partially disposed within the gap, and the exhaust nozzle assembly is free of the actuator.

公开(公告)号：US20240125286A1

公开(公告)日：2024-04-18

申请号：US18307162

申请日：2023-04-26

Applicant: Gulfstream Aerospace Corporation

Inventor： Derek Muzychka ,  Donald Freund ,  Andrew Clemens ,  John Louis ,  Joseph Gavin ,  Till Gerhardt ,  William Mcfarland ,  Benjamin Walke

IPC: F02K1/76 ,  B64C7/02 ,  F02K1/72

CPC classification number: F02K1/763 ,  B64C7/02 ,  F02K1/72 ,  F05D2220/323

Abstract: A nozzle assembly includes a sleeve defining a pathway, the sleeve disposed within a nacelle. The pathway and an internal surface of the nacelle guides a mass flow from an engine to an exit of the propulsion system. The sleeve is configured to move between a forward position an aft position within the nacelle aft of the engine. The sleeve has a protruding portion that extends towards a center of the pathway and that defines a smallest internal diameter of the sleeve. The sleeve includes a plurality of sleeve segments that are longitudinally aligned and circumferentially arranged to form the sleeve. The sleeve segments are configured to move circumferentially closer as the sleeve moves in a first direction within the nacelle and to move circumferentially further apart as the sleeve moves in a second direction within the nacelle. An actuator is coupled with, and is configured to move the sleeve.

公开(公告)号：US20230120249A1

公开(公告)日：2023-04-20

申请号：US17451137

申请日：2021-10-15

Applicant: Gulfstream Aerospace Corporation

Inventor： Shawn Bennett ,  Joe Gavin ,  Nicholas Powell ,  Donald Freund ,  Derek Muzychka ,  John Louis

IPC: F02C7/042 ,  B64D27/20 ,  F02K1/72 ,  F02K1/76 ,  F02K1/12 ,  F02C7/057

Abstract: An aircraft propulsion system includes an engine. The propulsion system further includes an inlet having a forward cowl lip and an aft cowl lip. The forward cowl lip moves between retracted and deployed positions. The forward cowl lip is adjacent to the aft cowl lip when retracted. The forward cowl lip is spaced apart from the aft cowl lip when deployed. The forward cowl lip has a smaller radius of curvature than the aft cowl lip. The propulsion system further includes a controller coupled with the engine and inlet. The controller restricts the maximum thrust commanded position of the engine when the aircraft is on the ground and moving below a predetermined speed. The controller lifts the restriction when the aircraft is moving at at least the predetermined speed. The controller controls the inlet to deploy the cowl lip when the aircraft is on the ground.