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公开(公告)号：US12237649B2
公开(公告)日：2025-02-25
申请号：US18191181
申请日：2023-03-28
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Sarmad Khan
IPC: H01T13/22 , F02C7/264 , F02C7/266 , F02K9/95 , H01T13/40 , H01T13/41 , H01T13/42 , H01T13/50 , H01T13/52
Abstract: The igniter can have a first conductor having a tip extending along an axis and forming a positive terminal; a second conductor having a tip surrounding the tip of the first conductor around the axis and forming a negative terminal; an insulator filling a space between the first conductor and the second conductor, a spark path extending radially, relative the axis, between the tip of the first conductor and the tip of the second conductor, from the positive terminal to the negative terminal; at least one magnet operable to generate a magnetic field B, the magnetic field B having a magnetic field orientation extending circumferentially around the axis, the at least one magnet disposed radially, relative the axis, between the first conductor and the second conductor, the at least one magnet embedded within the insulator.
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公开(公告)号：US12072261B2
公开(公告)日：2024-08-27
申请号：US17904342
申请日：2021-02-18
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Josselin Xavier Coupard , François Maurice Marcel Demaison , Valentin Francis Joël Facquet , Marion Marguerite Jedruszek
CPC classification number: G01M15/14 , F02C7/266 , F05D2220/323 , F05D2260/80
Abstract: Method for monitoring an ignition system of an aircraft turbine engine, the ignition system including a combustion chamber fitted with a spark plug and an ignition casing, the turbine engine including an accelerometer and an acoustic sensor. The method includes steps of: acquiring accelerometric and acoustic data representative of spark plug breakdown noises from signals generated by the accelerometer and the acoustic sensor, detecting breakdown peak times from the accelerometric data and the acoustic data, correlating the breakdown peak times detected from the accelerometric data and the breakdown peak times detected from the acoustic data, and establishing a diagnosis of the health of the ignition casing and a diagnosis for the spark plug on the basis of the correlation results.
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公开(公告)号：US12044180B2
公开(公告)日：2024-07-23
申请号：US17975110
申请日：2022-10-27
Applicant: General Electric Company
Inventor： Lucas John Stoia , Yimin Huang , Abdul Khan , Thomas Edward Johnson , Heath M. Ostebee , Jayaprakash Natarajan
Abstract: An igniter for a combustor of a turbomachine includes a fuel inlet in fluid communication with a mixing plenum. The mixing plenum is positioned upstream of a mixing channel. An air inlet is in fluid communication with the mixing plenum and an ignition source is in operative communication with the mixing channel. The igniter may include a mounting flange configured for coupling the igniter to the combustor. The ignition source may be positioned proximate to a downstream end of the mixing channel and upstream of the mounting flange. The mixing channel may define a venturi shape. The venturi shape includes a converging section between an upstream end of the mixing channel and a venturi throat.
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公开(公告)号：US20230392553A1
公开(公告)日：2023-12-07
申请号：US18186161
申请日：2023-03-18
Applicant: Acutronic Turbines Inc.
Inventor： Mark Harris , Patrick Bailey , David Monk , Felipe Gomez del Campo , Drew Weibel , Ilya Gulko , Munetake Nishihara , Ford McClure
CPC classification number: F02C7/266 , F23R3/16 , F05D2260/99 , F23R2900/00008
Abstract: An ignition and combustion assist system and method comprising a plasma igniter and electronic driver unit for use with gas turbine engines operating under low air densities, reduced voltage conditions and overall pressure ratios of 3:1 to 7:1. The plasma igniter has an inner chamber housing a centrally positioned and electrically isolated electrode attached to an electrical lead, driver unit, and AC or DC power supply. The electrode features a corner positioned near an outlet end of the igniter, where a plasma arc ignites a fuel-air mixture creating a flame extending into a primary burn region of a combustor of the gas turbine. The driver unit is in two embodiments and configured with low-cost microsecond voltage wave time periods or energy-efficient nano-second pulses. The method uses the plasma igniter and the electronic driver units described herein separately with other components or together.
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公开(公告)号：US11725586B2
公开(公告)日：2023-08-15
申请号：US16517090
申请日：2019-07-19
Inventor： Andrew D. Lowery , James E. Smith
IPC: F02C7/266 , F23R3/00 , F23R3/28 , H01P7/04 , H01P7/06 , H05H1/46 , H01Q1/44 , H01Q13/08 , H05H1/24
CPC classification number: F02C7/266 , F23R3/002 , F23R3/28 , H01P7/04 , H01P7/06 , H01Q1/44 , H01Q13/08 , H05H1/2441 , H05H1/46 , F05D2240/35 , F05D2260/99 , F23R2900/00008 , F23R2900/00009 , H05H1/463 , H05H1/4645 , H05H1/47
Abstract: An example system and corresponding method can include a combustion chamber of jet engine, a radio-frequency power source, and a resonator. The combustion chamber can include a liner defining a combustion zone, and include a fuel inlet configured to introduce fuel into the combustion zone. The resonator can have a resonant wavelength and include: a first conductor, a second conductor, a dielectric, and an electrode coupled to the first conductor. The resonator can be configured such that, when the resonator is excited by the radio-frequency power source with a signal having a wavelength proximate to an odd-integer multiple of one-quarter (¼) of the resonant wavelength, the resonator provides a plasma corona in the combustion zone. The controller can be configured to cause the radio-frequency power source to excite the resonator with the signal so as to provide the plasma corona.
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Patent Agency Ranking
公开(公告)号：US11702980B2
公开(公告)日：2023-07-18
申请号：US16838780
申请日：2020-04-02
Inventor： Ning Feng , Qili Cui , Ting Zhang , Libin Zhou , Wanchun Zha , Qiong Wu , Tao Kou , Xin Li , Tao Zhang , Lili Wang , Shuzhen Cui
CPC classification number: F02C6/00 , F02C7/12 , F02C7/266 , H02K7/1823 , F05D2220/76
Abstract: The present invention discloses a mobile power system, the whole mobile power system is assigned onto two transport vehicles, achieving effective integration to reduce transport vehicle and transport cost; the two transport vehicles are connected at the side to enable quick and convenient connection in working state, greatly saving installation time; a gas turbine starter is disposed on an exhaust auxiliary transportation unit so that the mobile power system can be started by a gas turbine in totally power failure conditions.
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7.发明公开公开(公告)号：US20230193829A1
公开(公告)日：2023-06-22
申请号：US17589145
申请日：2022-01-31
Applicant: General Electric Company
Inventor： Krishnakumar Venkatesan , Michael A. Benjamin , Michael T. Bucaro
Abstract: A turbine engine comprising a compressor section, a combustion section having a combustor, and a turbine section in serial flow arrangement. The combustor having a combustion chamber, at least one fuel injector, at least one compressed air passage, and at least one igniter. The at least one igniter can be provided within a portion of the at least one fuel injector or the at least one compressed air passage.
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公开(公告)号：US11614034B2
公开(公告)日：2023-03-28
申请号：US17881683
申请日：2022-08-05
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Richard Freer , Kian McCaldon , Tin-Cheung John Hu , Michel Bousquet , André Fortin
Abstract: A gas turbine engine has: a casing; a combustor liner delimiting a combustion chamber; a fuel nozzle in fluid communication with the combustion chamber; and an igniter having a base, a glow plug heater rod extending from the base along an axis and terminating in a rod end, and a sleeve extending around the glow plug heater rod, the sleeve radially spaced apart from the glow plug heater rod by an annular gap, the sleeve defines fins circumferentially distributed around the axis, each two circumferentially adjacent fins of the fins spaced apart from one another by a spacing communicating with the annular gap, the fins extending in a direction having an axial component from roots to tips, the roots axially closer to the base than the tips, the rod end extending axially beyond the tips of the fins such that the rod end is located outside the annular gap.
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公开(公告)号：US11530647B2
公开(公告)日：2022-12-20
申请号：US17408905
申请日：2021-08-23
Inventor： Robert H. Perkinson , Richard Ullyott
Abstract: There is described a method and system for in-flight start of an engine. The method comprises rotating a propeller; generating electrical power at an electric generator embedded inside a propeller hub from rotation of the propeller; transmitting the electrical power from the electric generator to an engine starter mounted on a core of the engine via an electric power link; and driving the engine with the engine starter to a sufficient speed while providing fuel to a combustor to light the engine to achieve self-sustaining operation of the engine.
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公开(公告)号：US11525580B2
公开(公告)日：2022-12-13
申请号：US17125114
申请日：2020-12-17
Applicant: Delavan Inc.
Inventor： Jason Ryon , Brandon P. Williams , Lev Alexander Prociw
Abstract: An embodiment of a combustor for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case, a fuel nozzle at an upstream end of the combustor liner, a torch igniter within the combustor case, and a removable fuel injector. The torch igniter includes a combustion chamber, a cap configured to receive a removable fuel injector and a surface igniter, a tip, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip which fluidly connects the combustion chamber to the combustor. The removable fuel injector extends through a fuel injector opening of the combustor case. The diameter of the fuel injector opening is wider than a fuel injector diameter of the removable fuel injector.
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