公开(公告)号：US10184614B2

公开(公告)日：2019-01-22

申请号：US14655789

申请日：2013-11-26

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Michael Jay Epstein ,  Robert Harold Weisgerber

IPC: F17C9/02 ,  F17C13/00

Abstract: A method for managing boil-off from an LNG tank located on board of an aircraft. The method, including removing the boil-off from the aircraft and disposing of the removed boil-off from the aircraft and an equipment assembly for use with an aircraft having an on-board LNG tank with a vent system having an outlet coupling, including a removal system configured to remove boil-off from the aircraft and a disposal system configured to dispose of the boil-off.

公开(公告)号：US20180171816A1

公开(公告)日：2018-06-21

申请号：US15382817

申请日：2016-12-19

Applicant: General Electric Company

Inventor： Thomas Ory Moniz ,  Joseph George Rose ,  Robert Harold Weisgerber ,  Jeffrey Donald Clements ,  Brandon Wayne Miller

IPC: F01D17/04 ,  F02K3/06 ,  F02C7/36

CPC classification number: F01D17/04 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/32 ,  F05D2260/40311 ,  F05D2260/80 ,  F05D2270/331 ,  F05D2270/335

Abstract: A gas turbine engine includes a fan section having a fan rotatable with a fan shaft and a turbomachinery section having a turbine and a turbomachine shaft rotatable with the turbine. A power gearbox is also provided mechanically coupled to both the fan shaft and the turbomachine shaft such that the fan shaft is rotatable by the turbomachine shaft across the power gearbox. A torque monitoring system includes a gearbox sensor operable with a gear of the power gearbox and a shaft sensor operable with at least one of the turbomachine shaft or the fan shaft. The torque monitoring system determines an angular position of the gear of the gearbox relative to at least one of the fan shaft or the turbomachine shaft using the gearbox sensor and the shaft sensor to determine a torque within the gas turbine engine.

公开(公告)号：US09676491B2

公开(公告)日：2017-06-13

申请号：US14654685

申请日：2013-11-26

Applicant: General Electric Company

Inventor： Michael Jay Epstein ,  Adon Delgado, Jr. ,  Robert Harold Weisgerber

IPC: B64C17/10 ,  B64D37/14 ,  B64D37/30 ,  B64D37/02

CPC classification number: B64D37/30 ,  B64D37/02 ,  Y02T50/44 ,  Y02T90/44

Abstract: A method of managing evaporated cryogenic fuel in a storage tank of a cryogenic fuel system of an aircraft and an aircraft having at least one turbine engine providing propulsive force for the aircraft and a cryogenic fuel system including a passively cooled cryogenic fuel storage tank located within the aircraft, a pressure vent fluidly coupled to the cryogenic fuel storage tank and exhausting evaporated gas from the cryogenic fuel to define a natural gas vent stream, and a catalytic converter fluidly coupled to the pressure vent.

公开(公告)号：US10975717B2

公开(公告)日：2021-04-13

申请号：US15382817

申请日：2016-12-19

Applicant: General Electric Company

Inventor： Thomas Ory Moniz ,  Joseph George Rose ,  Robert Harold Weisgerber ,  Jeffrey Donald Clements ,  Brandon Wayne Miller

IPC: F01D17/04 ,  F02C7/36 ,  F02K3/06

Abstract: A gas turbine engine includes a fan section having a fan rotatable with a fan shaft and a turbomachinery section having a turbine and a turbomachine shaft rotatable with the turbine. A power gearbox is also provided mechanically coupled to both the fan shaft and the turbomachine shaft such that the fan shaft is rotatable by the turbomachine shaft across the power gearbox. A torque monitoring system includes a gearbox sensor operable with a gear of the power gearbox and a shaft sensor operable with at least one of the turbomachine shaft or the fan shaft. The torque monitoring system determines an angular position of the gear of the gearbox relative to at least one of the fan shaft or the turbomachine shaft using the gearbox sensor and the shaft sensor to determine a torque within the gas turbine engine.

公开(公告)号：US09701416B2

公开(公告)日：2017-07-11

申请号：US14655761

申请日：2013-11-26

Applicant: General Electric Company

Inventor： Michael Jay Epstein ,  Paul Bernard Stumbo ,  Robert Harold Weisgerber

IPC: B64D37/32 ,  B64D37/30 ,  F17C3/00 ,  F02C7/14 ,  F02C7/224 ,  F02C9/40

CPC classification number: B64D37/30 ,  B64D37/32 ,  F02C7/14 ,  F02C7/224 ,  F02C9/40 ,  F05D2260/213 ,  F05D2260/98 ,  F17C3/00 ,  Y02T50/44 ,  Y02T50/672 ,  Y02T50/676 ,  Y02T90/44

Abstract: An aircraft having a turbine engine having a bleed air output line, a cryogenic fuel system having a cryogenic fuel tank for storing cryogenic fuel and a supply line operably coupling the tank to the turbine engine, and an on board inert gas generating system (OBIGGS) fluidly coupled to the bleed air output and having a nitrogen rich stream output line and an oxygen rich stream output line.