US20160153661A1 - Helmholtz damper and gas turbine with such a helmholtz damper - Google Patents

Helmholtz damper and gas turbine with such a helmholtz damper Download PDF

Info

Publication number
US20160153661A1
US20160153661A1 US14/934,277 US201514934277A US2016153661A1 US 20160153661 A1 US20160153661 A1 US 20160153661A1 US 201514934277 A US201514934277 A US 201514934277A US 2016153661 A1 US2016153661 A1 US 2016153661A1
Authority
US
United States
Prior art keywords
damper
combustor
helmholtz
piston
volume
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US14/934,277
Other languages
English (en)
Inventor
Mirko Ruben Bothien
Andre Theuer
Jost IMFELD
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
GE Vernova GmbH
Ansaldo Energia IP UK Ltd
Original Assignee
General Electric Technology GmbH
Alstom Technology AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Technology GmbH, Alstom Technology AG filed Critical General Electric Technology GmbH
Assigned to ALSTOM TECHNOLOGY LTD reassignment ALSTOM TECHNOLOGY LTD ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BOTHIEN, MIRKO RUBEN, Imfeld, Jost, THEUER, ANDRE
Assigned to GENERAL ELECTRIC TECHNOLOGY GMBH reassignment GENERAL ELECTRIC TECHNOLOGY GMBH CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: ALSTOM TECHNOLOGY LTD
Publication of US20160153661A1 publication Critical patent/US20160153661A1/en
Assigned to ANSALDO ENERGIA IP UK LIMITED reassignment ANSALDO ENERGIA IP UK LIMITED ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: GENERAL ELECTRIC TECHNOLOGY GMBH
Abandoned legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00013—Reducing thermo-acoustic vibrations by active means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

  • the present invention relates to the field of combustion technology. It refers to a Helmholtz damper according to the preamble of claim 1 .
  • FIG. 1 shows in a perspective view an exemplary stationary or industrial gas turbine of the GT13 E2 type.
  • the gas turbine 10 comprises in a casing 13 a rotor 12 , which rotates around a machine axis and defines within the casing 13 an annular hot gas channel extending in axial direction through the machine.
  • a compressor 14 with several stages of running blades compresses air, which enters the machine through an air inlet 11 .
  • the compressed air with a compressor outlet pressure pk 2 fills a plenum and enters a combustor 15 , where it is mixed with a fuel supplied by a plurality of burners 16 .
  • the burners 16 are configured as so-called AEV (or Advanced Environmental Vortex) burners, which are described for example in document WO 2009/109454.
  • FIG. 2 shows the main parameters of a generic Helmholtz damper configuration.
  • the Helmholtz damper 20 of FIG. 2 comprises a damper volume 21 with a volume V, which is in fluidic connection with a damped space (combustor) 19 via a neck tube 22 of length L N and inner diameter D N ; u denotes the bias mean flow.
  • the resonance frequency f of this damper can be approximately calculated by the formula:
  • Helmholtz damper 20 When Helmholtz damper 20 is attached to the combustor 15 of gas turbine 10 of FIG. 1 , it is surrounded by the plenum of the gas turbine, which is filled with compressed air of compressor outlet pressure pk 2 . Cooling air is introduced into damper volume 21 through an orifice 23 , which experiences a pressure drop ⁇ p due to the difference between the (higher) compressor outlet pressure pk 2 and the (lower) pressure within the combustion chamber of the combustor.
  • the frequency of the pulsations within the combustor depends on the operation mode of the gas turbine. Especially, there is a change in pulsation frequency f P , when the gas turbine changes from part load operation to base load operation, and vice versa. For a gas turbine of the type shown in FIG. 1 there can be a change of up to 20% of pulsation frequency f P between part load and base load, with the pulsation frequency increasing with growing load.
  • the resonance frequency of the dampers should stay tuned to the pulsation frequency even if the load conditions of the gas turbine change.
  • the damper volume V should be changed in accordance with a change in the load conditions.
  • Document EP 2 397 761 A1 discloses a Helmholtz damper and a method for regulating the resonance frequency of a Helmholtz damper.
  • it refers to Helmholtz dampers to be connected to lean premixed, low emission combustion systems of gas turbines, whereby said Helmholtz damper comprises an enclosure from which a neck extends, and a pipe is inserted into and fits the neck.
  • an actuator is connected to the pipe to adjust its portion inserted into the neck.
  • Document EP 2 397 760 A1 discloses a damper arrangement that has a first Helmholtz damper connected in series to a second Helmholtz damper. The resonance frequency of the first Helmholtz damper and the resonance frequency of the second Helmholtz damper are shifted from one another in an amount producing a synergic damping effect.
  • Document DE 100 26 121 A1 describes an apparatus for damping acoustic vibrations in a combustor as well as a corresponding combustor arrangement with the apparatus.
  • the apparatus comprises a Helmholtz resonator that can be connected via a connecting channel with a combustor.
  • the Helmholtz resonator contains a hollow body the volume of which can be changed by adding or draining a fluid via a supply line, or is located adjacent to such a hollow body in such a way that the resonance volume of the Helmholtz resonator is changed when the volume of the hollow body is changed.
  • This apparatus makes it possible to adjust the resonance frequency of a Helmholtz resonator arranged inside a pressure container in accordance with the respective current operating point of the combustor to be damped, without having to pass movable components through the pressure container.
  • Document U.S. Pat. No. 8,661,822 B2 discloses a system with a turbine engine, comprising: a compressor; a turbine; a combustor disposed downstream from the compressor and upstream from the turbine; a fluid injection system configured to inject one or more fluids into the combustor; a variable geometry resonator coupled to the fluid injection system; and a controller configured to tune the variable geometry resonator in response to feedback.
  • the Helmholtz damper according to the invention which is especially suitable for damping pulsations in a combustor of a gas turbine, comprises a damper volume, which can be connected to a damped space by means of a neck tube, and further comprises a piston, which is moveable within said damper volume and divides said damper volume into a variable first part on one side of said piston, which variable first part is connected to said neck tube, and a correspondingly variable second part on the other side of said piston. It is characterized in that said piston is driven by a pressure drop between said first and second part of said damper volume.
  • An embodiment of the Helmholtz damper according to the invention is characterized in that the piston is held in an idle position, where the first part of said damper volume is a maximum, by means of a spring, and that said pressure drop drives said piston against the force of said spring.
  • said spring is arranged within said first part of said damper volume.
  • said spring may be arranged outside of said damper volume and acts on said piston via a piston rod, which extends from said piston to the outside of said damper volume.
  • said spring is a helical spring.
  • Another embodiment of the Helmholtz damper according to the invention is characterized in that said second part of said damper volume is in fluidic connection with the outside of said damper volume.
  • said damper volume is enclosed by a housing, and said fluidic connection is established by at least one opening in said housing.
  • the gas turbine according to the invention comprises a compressor, at least one combustor and a turbine, whereby said at least one combustor is enclosed by a combustor casing, the outside of which is exposed to the compressor outlet pressure of said compressor, whereby at least one Helmholtz damper is provided at and connected to one combustor in order to damp pulsations within said combustor.
  • said at least one Helmholtz damper is a Helmholtz damper according to the invention, and that a pressure drop between said compressor outlet pressure and the pressure within said combustor is used to drive said piston of said at least one Helmholtz damper.
  • An embodiment of the gas turbine according to the invention is characterized in that said at least one Helmholtz damper is attached to the combustor casing by adaptation means.
  • said at least one Helmholtz damper is connected to said combustor through a hole in said combustor casing, and said adaptation means comprises an insert, which fits into said hole and receives a neck tube of said at least one Helmholtz damper such that said neck tube passes through said insert to open out into said combustor.
  • a neck tube adapter is provided to seal said neck tube against said insert.
  • said neck tube is releasably connected to the damper volume of said at least one Helmholtz damper.
  • Another embodiment of the gas turbine according to the invention is characterized in that said combustor is of an annular configuration, and that a plurality of Helmholtz dampers are circumferentially arranged around said combustor.
  • FIG. 1 shows in a perspective view a stationary gas turbine of the GT13 E2 type, which is suitable for being used with Helmholtz dampers according to the invention
  • FIG. 2 shows the main parameters of a basic Helmholtz damper configuration
  • FIG. 3 shows an example of the absolute pressure drop ⁇ p as a function of relative gas turbine load for an exemplary gas turbine
  • FIG. 4 shows an embodiment of the Helmholtz damper according to the invention with the piston (a) in a starting position and (b) in an active position driven by a certain pressure drop ⁇ p;
  • FIG. 5 shows a Helmholtz damper according to another embodiment of the invention attached and coupled to the combustor of a gas turbine of the type shown in FIG. 1 ;
  • FIG. 6 shows (a) in detail the Helmholtz damper of FIG. 5 and (b) in even more detail the piston of said damper;
  • FIG. 7 shows a Helmholtz damper according to a further embodiment of the invention attached and coupled to a can combustor.
  • FIG. 3 shows the results of measurements of the absolute pressure drop ⁇ p as a function of relative gas turbine load for an exemplary gas turbine.
  • the invention seeks to explore this fact in such a way that the volume V of the damper is reduced so that its resonance frequency is continuously adjusted in order to provide highest damping at the required frequency. This is possible due to the fact that the outside of the damper volume is exposed the compressor outlet pressure pk 2 , whereas the pressure inside the damper is very close to that of the combustion chamber.
  • FIG. 4 shows an embodiment of the Helmholtz damper according to the invention.
  • FIG. 4( a ) shows the damper in a starting position with its damper volume being a maximum.
  • FIG. 4( b ) shows the damper in an active position, wherein the damper volume has been automatically reduced due to an increased pressure drop ⁇ p between inside and outside of the damper.
  • the Helmholtz damper 24 according to FIG. 4 comprises damper volume 25 , which is enclosed by a housing 25 a.
  • the damper volume 25 is divided by means of a piston 27 which is moveable within said damper volume 25 , into a variable first part V 1 on one side of the piston 27 , and a correspondingly variable second part V 2 on the other side of said piston 27 .
  • the variable first part V 1 is connected to a neck tube 26 of said Helmholtz damper 24 .
  • the variable second part V 2 is connected to the outside of Helmholtz damper 24 by means of openings 31 provided in housing 25 a.
  • combustor pressure p C acts through neck tube 26 on one side of piston 27 with area A 2
  • An orifice 32 may be provided through piston 27 to allow the access of some cooling air.
  • the volume is defined by diameter D or area A 1 and height H 1 .
  • the damper volume (V 1 ) has been decreased to A 2 ⁇ H 2 .
  • the driving force of pressure drop ⁇ p on piston 27 is balanced by the spring force of a helical spring 30 , which is in this case arranged outside the damper volume and is compressed, when piston 27 leaves its starting position.
  • the spring 30 is arranged between the top of housing 25 a and a bearing plate 29 at the end of a piston rod 28 , which extends from piston 27 to the outside of damper volume 25 and serves to couple the balancing spring force to piston 27 .
  • FIGS. 5 and 6 A more compact design of a Helmholtz damper according to the invention, which is more suitable for being applied to a gas turbine combustor 33 , is shown in FIGS. 5 and 6 .
  • Helmholtz damper 38 of FIGS. 5 and 6 is attached to combustor casing 34 at a place, where the hot gas 39 is guided to combustor outlet 35 .
  • Helmholtz damper 38 comprises a damper volume 40 enclosed by a housing 40 a, and divided by a piston 44 .
  • Housing 40 a is on its upper side in fluidic connection with the environment (plenum pressure pk 2 ) by means of a wide opening 46 . At its lower side, it is closed by a bowl-like base element 41 .
  • a separate neck tube 43 which extends from the combustion chamber into the interior of damper volume 40 , connects the damper volume with the combustor.
  • Neck tube 43 is fixed in a neck tube adapter 42 , which is held between base element 41 and an insert 37 that is used to mount the damper arrangement in a hole 36 in the combustor casing 34 .
  • the neck tube 43 may be of any cross-sectional shape.
  • Piston 44 which has an orifice 47 for cooling purposes, is designed as a free piston.
  • a balancing helical spring 45 is arranged within the damper volume 40 . This configuration with a free piston and an internal balancing spring is on one hand very compact, requiring only minimal space, and on the other hand is protected against impacts from outside.
  • FIG. 7 schematically illustrates a Helmholtz damper 48 attached to a can combustor 49 .
  • Arrow 39 represents the hot gas flow.
  • the damper 48 is circumferentially arranged around the can combustor 49 , forming an annular damper volume 40 , surrounding the combustion chamber or hot gas path respectively.
  • At least one neck tube 43 of any cross-sectional design connects the space 19 , to be damped, with the variable first part V 1 of the damper volume 40 .
  • At least one opening 46 connects the variable second volume V 2 with an environment outside of the Helmholtz damper 48 .
  • the variable first part V 1 of the damper volume 40 and the variable second part V 2 of the damper volume 40 are separated by the piston 44 .
  • the piston 44 is arranged and designed to perform a movement parallel to the axis of the combustor 49 , thereby interacting with the balancing spring 45 of the helical type, arranged within the damper volume 40 along the lateral surface area of the damper housing 40 a.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Fluid-Damping Devices (AREA)
  • Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
US14/934,277 2014-12-01 2015-11-06 Helmholtz damper and gas turbine with such a helmholtz damper Abandoned US20160153661A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP14195660.7 2014-12-01
EP14195660.7A EP3029376B1 (de) 2014-12-01 2014-12-01 Gasturbine mit einem Helmholtz-Resonator

Publications (1)

Publication Number Publication Date
US20160153661A1 true US20160153661A1 (en) 2016-06-02

Family

ID=51999337

Family Applications (1)

Application Number Title Priority Date Filing Date
US14/934,277 Abandoned US20160153661A1 (en) 2014-12-01 2015-11-06 Helmholtz damper and gas turbine with such a helmholtz damper

Country Status (3)

Country Link
US (1) US20160153661A1 (de)
EP (1) EP3029376B1 (de)
CN (1) CN105650192B (de)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles
US20230175692A1 (en) * 2021-12-06 2023-06-08 Ge Avio S.R.L. Dome-integrated acoustic damper for gas turbine combustor applications
US20230400187A1 (en) * 2022-06-08 2023-12-14 General Electric Company Combustor with a variable volume primary zone combustion chamber
US20230407819A1 (en) * 2022-06-17 2023-12-21 Blue Origin, Llc Multi-volume acoustic resonator for rocket engine
US20250334269A1 (en) * 2024-04-26 2025-10-30 Rtx Corporation Sieve rde injector with variable pressure drop capability

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2557264B (en) * 2016-12-02 2020-04-08 Delphi Tech Ip Ltd Multi-Chamber Helmholtz Resonator
RU2687545C1 (ru) * 2018-08-17 2019-05-14 Рафаэль Салихзянович Кашапов Малоэмиссионная камера сгорания и способ подачи в ней топлива
JP7131396B2 (ja) * 2019-01-08 2022-09-06 トヨタ自動車株式会社 トランスミッションの防音装置
CN113482777B (zh) * 2021-06-28 2022-09-06 浙江大学 一种带偏流的颈部优化亥姆霍兹消声器及应用

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4178562A (en) * 1977-01-10 1979-12-11 Tavkozlesi Kutato Intezet Cavity resonators with frequency-linear tuning
US4881572A (en) * 1987-04-03 1989-11-21 Stifab Ab System for controlling automatically the setting of a damper in a ventilation duct
US6530221B1 (en) * 2000-09-21 2003-03-11 Siemens Westinghouse Power Corporation Modular resonators for suppressing combustion instabilities in gas turbine power plants
US6634457B2 (en) * 2000-05-26 2003-10-21 Alstom (Switzerland) Ltd Apparatus for damping acoustic vibrations in a combustor
US8973365B2 (en) * 2010-10-29 2015-03-10 Solar Turbines Incorporated Gas turbine combustor with mounting for Helmholtz resonators

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1624250A1 (de) * 2004-08-03 2006-02-08 Siemens Aktiengesellschaft Vorrichtung zur Dämpfung von thermoakustichen Schwingungen in Brennkammern
EP2257736B1 (de) 2008-03-07 2015-11-25 Alstom Technology Ltd Verfahren zum erzeugen von heissgas
RU2508506C2 (ru) 2009-09-01 2014-02-27 Дженерал Электрик Компани Способ и установка для ввода текучей среды в камеру сгорания газотурбинного двигателя
EP2397760B1 (de) * 2010-06-16 2020-11-18 Ansaldo Energia IP UK Limited Dämpfungsanordnung und Verfahren zu deren Entwurf
EP2397761B1 (de) 2010-06-16 2021-10-06 Ansaldo Energia Switzerland AG Helmholtz-Dämpfer
CN103241093B (zh) * 2013-04-10 2015-09-02 华南理工大学 一种车用减震器及利用该车用减震器发电的装置

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4178562A (en) * 1977-01-10 1979-12-11 Tavkozlesi Kutato Intezet Cavity resonators with frequency-linear tuning
US4881572A (en) * 1987-04-03 1989-11-21 Stifab Ab System for controlling automatically the setting of a damper in a ventilation duct
US6634457B2 (en) * 2000-05-26 2003-10-21 Alstom (Switzerland) Ltd Apparatus for damping acoustic vibrations in a combustor
US6530221B1 (en) * 2000-09-21 2003-03-11 Siemens Westinghouse Power Corporation Modular resonators for suppressing combustion instabilities in gas turbine power plants
US8973365B2 (en) * 2010-10-29 2015-03-10 Solar Turbines Incorporated Gas turbine combustor with mounting for Helmholtz resonators

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles
US20230175692A1 (en) * 2021-12-06 2023-06-08 Ge Avio S.R.L. Dome-integrated acoustic damper for gas turbine combustor applications
US20230400187A1 (en) * 2022-06-08 2023-12-14 General Electric Company Combustor with a variable volume primary zone combustion chamber
US11898755B2 (en) * 2022-06-08 2024-02-13 General Electric Company Combustor with a variable volume primary zone combustion chamber
US20230407819A1 (en) * 2022-06-17 2023-12-21 Blue Origin, Llc Multi-volume acoustic resonator for rocket engine
US11867139B1 (en) * 2022-06-17 2024-01-09 Blue Origin, Llc Multi-volume acoustic resonator for rocket engine
US20240191676A1 (en) * 2022-06-17 2024-06-13 Blue Origin, Llc Multi-volume acoustic resonator for rocket engine
US12146454B2 (en) * 2022-06-17 2024-11-19 Blue Origin, Llc Multi-volume acoustic resonator for rocket engine
US20250334269A1 (en) * 2024-04-26 2025-10-30 Rtx Corporation Sieve rde injector with variable pressure drop capability

Also Published As

Publication number Publication date
CN105650192A (zh) 2016-06-08
CN105650192B (zh) 2020-03-03
EP3029376B1 (de) 2018-10-03
EP3029376A1 (de) 2016-06-08

Similar Documents

Publication Publication Date Title
EP3029376B1 (de) Gasturbine mit einem Helmholtz-Resonator
JP4880825B2 (ja) 燃焼器内の音響振動を減衰するための装置
US10088165B2 (en) System and method for tuning resonators
RU2508506C2 (ru) Способ и установка для ввода текучей среды в камеру сгорания газотурбинного двигателя
EP2397761B1 (de) Helmholtz-Dämpfer
US7966994B2 (en) System for metering a fuel supply
US20050199439A1 (en) Variable geometry resonator for acoustic control
EP2397760A1 (de) Dämpfungsanordnung und Verfahren zu deren Entwurf
KR102055493B1 (ko) 연소기 및 가스 터빈
EP2865948B1 (de) Gasturbinenbrennkammer mit Viertelwellen-Dämpfer
US10167780B2 (en) Tunable resonator
US20160076766A1 (en) Combustion system of a flow engine and method for determining a dimension of a resonator cavity
CN103423492B (zh) 调压阀
JP2012117807A (ja) 広帯域周波数応答の調整可能な共振器
CN106594798B (zh) 用于燃烧室的阻尼器组件
US20080118343A1 (en) Combustion control for a gas turbine
EP2667096A2 (de) Turbomaschinenbrennkammer und Verfahren zur Einstellung der Verbrennungsdynamik darin
JP3233798B2 (ja) 燃焼器の燃焼振動・圧力変動低減装置
JP2016173099A (ja) 圧縮機用の吸気調整弁
JP6066754B2 (ja) 音響ダンパ、燃焼器およびガスタービン並びに音響ダンパのターゲット周波数変更方法
RU2002132943A (ru) Клапан регулирования тяги со снижением коэффициента усиления для ракетного двигателя и регулятор потока для него

Legal Events

Date Code Title Description
AS Assignment

Owner name: ALSTOM TECHNOLOGY LTD, SWITZERLAND

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:BOTHIEN, MIRKO RUBEN;THEUER, ANDRE;IMFELD, JOST;REEL/FRAME:037168/0708

Effective date: 20151119

AS Assignment

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, SWITZERLAND

Free format text: CHANGE OF NAME;ASSIGNOR:ALSTOM TECHNOLOGY LTD;REEL/FRAME:038216/0193

Effective date: 20151102

AS Assignment

Owner name: ANSALDO ENERGIA IP UK LIMITED, GREAT BRITAIN

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:GENERAL ELECTRIC TECHNOLOGY GMBH;REEL/FRAME:041731/0626

Effective date: 20170109

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION