公开(公告)号：US20170219080A1

公开(公告)日：2017-08-03

申请号：US15008922

申请日：2016-01-28

Applicant: General Electric Company

Inventor： Daniel Alan Niergarth ,  Brandon Wayne Miller ,  Bugra Han Ertas ,  Donald Albert Bradley ,  Joseph Robert Dickman

IPC: F16H57/00 ,  F16H57/08 ,  F02C7/36 ,  F16H1/28

CPC classification number: F16H57/0006 ,  F02C7/36 ,  F05D2260/40311 ,  F05D2260/96 ,  F16C19/28 ,  F16C27/045 ,  F16C2361/61 ,  F16H1/28 ,  F16H57/0471 ,  F16H57/082 ,  F16H2057/0012

Abstract: An epicyclic gearing arrangement includes a planet gear rotatable on a planet bearing that is mounted via a support pin to a carrier of the epicyclic gearing arrangement. A spring film damper is disposed between the outer surface of the bearing's outer ring and the opposing inner surface of the planet gear and includes an annular gap. The support pin and/or outer ring include oil feed holes that open into the respective annular gap(s).

公开(公告)号：US20170167507A1

公开(公告)日：2017-06-15

申请号：US14963924

申请日：2015-12-09

Applicant: General Electric Company

Inventor： Daniel Alan Niergarth ,  Brandon Wayne Miller ,  Darek Tomasz Zatorski ,  Christopher James Kroger

IPC: F04D29/36 ,  F04D29/38 ,  F04D29/32

CPC classification number: F04D29/362 ,  B64C11/38 ,  F01D7/00 ,  F02K3/06 ,  F04D29/323 ,  F04D29/325 ,  F04D29/38 ,  F05D2220/36 ,  F05D2260/74 ,  F05D2260/76 ,  F05D2270/64 ,  Y02T50/673

Abstract: A method of transferring a fluid flow from a stationary member to an adjacent rotatable member and a fluid flow transfer system are provided. The system includes one or more fluid supply conduits and a gearbox flow path configured to channel the flow of fluid through the power gearbox. The system also includes a transfer sleeve device configured to receive the flow of fluid from the gearbox flow path. The transfer sleeve device includes a stationary transfer sleeve member and a rotatable transfer sleeve member. The transfer sleeve device is configured to transfer the flow of fluid between the stationary transfer sleeve member and the rotatable transfer sleeve member. A pitch change mechanism (PCM) actuator is configured to receive the flow of fluid through one or more of a plurality of flow ports wherein the plurality of flow ports direct the flow of fluid to a respective actuator.

公开(公告)号：US12044194B2

公开(公告)日：2024-07-23

申请号：US16811368

申请日：2020-03-06

Applicant: General Electric Company

Inventor： David Marion Ostdiek ,  Alan Roy Stuart ,  Daniel Alan Niergarth ,  Gert Johannes van der Merwe ,  Brandon Wayne Miller ,  Stephen William Freund

IPC: F02K3/077 ,  B64D27/10 ,  F02C3/073 ,  F02K1/34 ,  F02K3/02 ,  F02K3/072 ,  F02K3/075

CPC classification number: F02K3/072 ,  B64D27/10 ,  F02C3/073 ,  F02K1/34 ,  F02K3/025 ,  F02K3/075 ,  F02K3/077

Abstract: A propulsion system, the propulsion system comprising a rotating element, a stationary element, and an inlet between the rotating element and the stationary element, wherein the inlet passes radially inward of the stationary element; wherein the inlet passes radially inward of the stationary element; wherein the inlet leads to an inlet duct containing a ducted fan having an axis of rotation and a plurality of blades; and wherein the inlet duct divides into a first duct and a second duct, separate from the first duct. A method of operating a propulsion system, comprising the steps of: operating a first rotating fan assembly to produce a first stream of air; directing a portion of the first stream of air into a second ducted rotating fan assembly; operating the second ducted rotating fan assembly to produce a second stream of air; dividing the second stream of air into a core stream and a fan stream; and directing the core stream into a gas turbine engine core.

公开(公告)号：US11815024B2

公开(公告)日：2023-11-14

申请号：US17375489

申请日：2021-07-14

Applicant: General Electric Company

Inventor： Daniel Alan Niergarth ,  Adon Delgado, Jr. ,  Brandon Wayne Miller ,  Hendrik Pieter Jacobus de Bock

IPC: F02C7/224 ,  F02C7/141 ,  F28F23/00 ,  F02C7/14 ,  F28F27/02

CPC classification number: F02C7/224 ,  F02C7/14 ,  F02C7/141 ,  F28F23/00 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2260/213 ,  F28F27/02 ,  F28F2250/06

Abstract: A gas turbine engine includes a turbomachine and a thermal management system. The thermal management system includes a heat source heat exchanger configured to collect heat from the turbomachine during operation; a heat sink heat exchanger; and a thermal transport bus having a heat exchange fluid configured to flow therethrough at a pressure within an operational pressure range. The thermal management system defines an operational temperature range for the heat exchange fluid, the operational temperature range having a lower temperature limit less than about zero degrees Fahrenheit at a pressure within the operational pressure range and an upper temperature limit of at least about 1000 degrees Fahrenheit at a pressure within the operational pressure range.

公开(公告)号：US11795964B2

公开(公告)日：2023-10-24

申请号：US17377668

申请日：2021-07-16

Applicant: General Electric Company

Inventor： Nicholas M. Daggett ,  Gert Johannes van der Merwe ,  Daniel Alan Niergarth ,  Brian Lewis Devendorf

IPC: B64C11/34 ,  F04D29/34 ,  F02C3/06 ,  B64C11/32 ,  F04D29/32 ,  F04D29/36

CPC classification number: F04D29/34 ,  F02C3/06 ,  B64C11/325 ,  B64C11/346 ,  F04D29/323 ,  F04D29/366 ,  F05D2220/32 ,  F05D2240/24

Abstract: A fan assembly for a gas turbine engine includes a fan disk, a trunnion, a fan blade, and a counterweight assembly. The fan disk is configured to rotate about an axial centerline of the gas turbine engine when installed in the gas turbine engine. The trunnion is mounted to the fan disk and defines a slot extending through a portion of the trunnion. The fan blade defines a pitch axis and is rotatably attached to the fan disk about its pitch axis through the trunnion. The counterweight assembly includes a link arm extending to the trunnion and an engagement device mounted to the link arm that is disposed to move through the slot of the trunnion.

公开(公告)号：US11725584B2

公开(公告)日：2023-08-15

申请号：US15873605

申请日：2018-01-17

Applicant: General Electric Company

Inventor： Daniel Alan Niergarth ,  Brandon Wayne Miller ,  Jeffrey Douglas Rambo ,  Matthew Robert Cerny

IPC: F02C7/14 ,  F02C9/18 ,  F02C7/18

CPC classification number: F02C7/14 ,  F02C7/185 ,  F02C9/18 ,  F05D2260/213 ,  F05D2270/301 ,  F05D2270/303

Abstract: A heat engine comprising a compressor providing a flow of compressed air from a core flowpath of the heat engine; a cooled cooling air (CCA) heat exchanger system to which the flow of compressed air is provided from the compressor; a coolant supply system providing a flow of coolant to the CCA heat exchanger in thermal communication with the flow of compressed air at the CCA heat exchanger, in which the coolant supply system and CCA heat exchanger together define a CCA circuit through which the compressed air flows in thermal communication with the coolant; and a hot section disposed downstream of the compressor section along the core flowpath through which combustion gases flow, in which the hot section defines a secondary flowpath through which the flow of compressed air from the CCA heat exchanger is provided.

公开(公告)号：US11702958B2

公开(公告)日：2023-07-18

申请号：US17483251

申请日：2021-09-23

Applicant: General Electric Company

Inventor： Scott Alan Schimmels ,  Daniel Alan Niergarth ,  Arthur William Sibbach ,  Brandon Wayne Miller

IPC: F01D25/12 ,  F01D25/10 ,  F02C7/12

CPC classification number: F01D25/10 ,  F01D25/12 ,  F02C7/12 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2260/213

Abstract: A method of regulating pressure in a thermal transport bus of a gas turbine engine, the method including: operating the gas turbine engine with the thermal transport bus having an intermediary heat exchange fluid flowing therethrough, the thermal transport bus including one or more heat source heat exchangers and one or more heat sink heat exchangers in thermal communication through the intermediary heat exchanger fluid; and adjusting a flow volume of the thermal transport bus using a variable volume device in fluid communication with the thermal transport bus in response to a pressure change associated with the thermal transport bus.

公开(公告)号：US20230091733A1

公开(公告)日：2023-03-23

申请号：US17483251

申请日：2021-09-23

Applicant: General Electric Company

Inventor： Scott Alan Schimmels ,  Daniel Alan Niergarth ,  Arthur William Sibbach ,  Brandon Wayne Miller

IPC: F01D25/10 ,  F02C7/12 ,  F01D25/12

Abstract: A method of regulating pressure in a thermal transport bus of a gas turbine engine, the method including: operating the gas turbine engine with the thermal transport bus having an intermediary heat exchange fluid flowing therethrough, the thermal transport bus including one or more heat source heat exchangers and one or more heat sink heat exchangers in thermal communication through the intermediary heat exchanger fluid; and adjusting a flow volume of the thermal transport bus using a variable volume device in fluid communication with the thermal transport bus in response to a pressure change associated with the thermal transport bus.

公开(公告)号：US11591965B2

公开(公告)日：2023-02-28

申请号：US17215130

申请日：2021-03-29

Applicant: General Electric Company

Inventor： Christopher Edward Wolfe ,  Hendrik Pieter Jacobus de Bock ,  William Dwight Gerstler ,  Brian Gene Brzek ,  Brandon Wayne Miller ,  Daniel Alan Niergarth ,  Kevin Robert Feldmann ,  Kevin Edward Hinderliter

IPC: F02C7/141 ,  F01P1/00

Abstract: A thermal management system for transferring heat between fluids includes a thermal transport bus through which a heat exchange fluid flows. Additionally, the system includes a heat source heat exchanger arranged along the bus such that heat is added to the fluid flowing through the heat source heat exchanger. Moreover, the system includes a plurality of heat sink heat exchangers arranged along the bus such that heat is removed from the fluid flowing through the plurality of heat sink heat exchangers. Furthermore, the system includes a bypass conduit fluidly coupled to the bus such that the bypass conduit allows the fluid to bypass one of the heat source heat exchanger or one of the heat sink heat exchangers. In addition, the system includes a valve configured to control a flow of the fluid through the bypass conduit based on a pressure of the fluid within the bus.

公开(公告)号：US20230043809A1

公开(公告)日：2023-02-09

申请号：US17388618

申请日：2021-07-29

Applicant: General Electric Company

Inventor： Scott Alan Schimmels ,  Jeffrey Douglas Rambo ,  Daniel Alan Niergarth ,  Daniel Lawrence Tweedt ,  Michael Simonetti ,  Michael Julian Castillo ,  Timothy Richard DePuy ,  Steven Benjamin Morris

IPC: F01N3/02 ,  F02C3/04

Abstract: A gas turbine engine is provided including a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order; a rotor assembly driven by the turbomachine, the rotor assembly, the turbomachine, or both comprising a substantially annular duct relative to the centerline of the gas turbine engine, the annular duct defining a flowpath; a heat exchanger positioned within the annular duct and extending substantially continuously along the circumferential direction, the heat exchanger comprising a first material defining a heat exchange surface exposed to the flowpath, wherein the first material defines a heat exchange coefficient and wherein the heat exchange surface defines a surface area (A), and wherein the heat exchanger has an effective transmission loss (ETL) of between 5 decibels and 1 decibel for an operating condition.