[go: up one dir, main page]

SA113340953B1 - ناقل للاحتراق متكيف ليوجه غازات الاحتراق في ممر تدفق غاز ساخن - Google Patents

ناقل للاحتراق متكيف ليوجه غازات الاحتراق في ممر تدفق غاز ساخن

Info

Publication number
SA113340953B1
SA113340953B1 SA113340953A SA113340953A SA113340953B1 SA 113340953 B1 SA113340953 B1 SA 113340953B1 SA 113340953 A SA113340953 A SA 113340953A SA 113340953 A SA113340953 A SA 113340953A SA 113340953 B1 SA113340953 B1 SA 113340953B1
Authority
SA
Saudi Arabia
Prior art keywords
combustor transition
side wall
combustor
flow path
gas flow
Prior art date
Application number
SA113340953A
Other languages
English (en)
Inventor
ميركو روبين بوتين
مايكل دوسينج
Original Assignee
أنسالدو إنيرجيا سويزرلاند إيه جي
جينيرال اليكتريك تيكنولوجي جي ام بي اتش
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 أنسالدو إنيرجيا سويزرلاند إيه جي, جينيرال اليكتريك تيكنولوجي جي ام بي اتش filed Critical أنسالدو إنيرجيا سويزرلاند إيه جي
Publication of SA113340953B1 publication Critical patent/SA113340953B1/ar

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/24—Heat or noise insulation
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • F05D2260/963—Preventing, counteracting or reducing vibration or noise by Helmholtz resonators
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Soundproofing, Sound Blocking, And Sound Damping (AREA)

Abstract

يتعلق الكشف بانتقال حراق (24) متكيف ليوجه غازات الاحتراق في ممر تدفق غاز ساخن (15) يمتد بين حراق أسطواني (2) ومرحلة أولى من التوربين (3) في توربين غازي (9). يضم انتقال الحراق (24) قناة تمتلك نهاية منبع متكيفة للاتصال مع الحراق الأسطواني (2) ونهاية مصب متكيفة للاتصال مع مرحلة أولى من التوربين (3), حيث أن نهاية المصب تضم جدار خارجي (11), جدار داخلي (12), جدار جانبي أول وثاني (21أ, 21ب). إن انتقال الحراق, يتميز في أن الجدار الجانبي الواحد على الأقل (21أ, 21ب) يمتلك توسع جدار جانبي (20, 20أ, 20ب), الذي يمتد في اتجاه مصب بعد المخرج (22). يحيط توسع الجدار الجانبي (20, 20أ, 20ب) جزئياً على الأقل بحجم مرنان أول (28) وتوسع جدار جانبي واحد على الأقل (20, 20أ, 20ب) يضم حفرة مرنان (26), الذي يهيأ كرقبة مخمد Helmholtz. وبالإضافة إلى انتقال الحراق (24) يتم الكشف عن توربين غازي يضم انتقال حراق (24) مماثل, طريقة من أجل التعديل التحديثي على التوربين الغازي (9) مع انتقال حراق (24) مماثل وطريقة للفحص بالأنبوب المنظار من GT مع انتقال حراق مماثل. (الشكل 3)
SA113340953A 2012-10-24 2013-10-23 ناقل للاحتراق متكيف ليوجه غازات الاحتراق في ممر تدفق غاز ساخن SA113340953B1 (ar)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12189722.7A EP2725196A1 (en) 2012-10-24 2012-10-24 Combustor transition

Publications (1)

Publication Number Publication Date
SA113340953B1 true SA113340953B1 (ar) 2016-01-19

Family

ID=47073337

Family Applications (1)

Application Number Title Priority Date Filing Date
SA113340953A SA113340953B1 (ar) 2012-10-24 2013-10-23 ناقل للاحتراق متكيف ليوجه غازات الاحتراق في ممر تدفق غاز ساخن

Country Status (8)

Country Link
US (1) US9429032B2 (ar)
EP (2) EP2725196A1 (ar)
JP (1) JP5726267B2 (ar)
KR (1) KR101576457B1 (ar)
CN (1) CN103775213B (ar)
CA (1) CA2830690C (ar)
RU (1) RU2552886C2 (ar)
SA (1) SA113340953B1 (ar)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015199694A1 (en) * 2014-06-26 2015-12-30 Siemens Energy, Inc. Converging flow joint insert system at an intersection between adjacent transitions duct bodies
WO2016057020A1 (en) * 2014-10-07 2016-04-14 Siemens Energy, Inc. Arrangement for a gas turbine combustion engine
EP3124749B1 (en) 2015-07-28 2018-12-19 Ansaldo Energia Switzerland AG First stage turbine vane arrangement
FR3068075B1 (fr) * 2017-06-23 2019-08-09 Safran Systeme de combustion a volume constant comprenant un element d'obturation tournant a lumieres segmentees
JP6871377B2 (ja) 2017-06-29 2021-05-12 三菱パワー株式会社 ガスタービンの１段静翼、ガスタービン、ガスタービンの静翼ユニット及び燃焼器アセンブリ
JP7045851B2 (ja) * 2017-12-28 2022-04-01 三菱重工業株式会社 燃焼器及びガスタービン
JP7232035B2 (ja) * 2018-12-18 2023-03-02 三菱重工業株式会社 ガスタービンの静翼及びガスタービン
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

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5402631A (en) 1991-05-10 1995-04-04 Praxair Technology, Inc. Integration of combustor-turbine units and integral-gear pressure processors
DE4446610A1 (de) 1994-12-24 1996-06-27 Abb Management Ag Verfahren zum Betrieb einer Gasturbogruppe
RU2219439C1 (ru) * 2002-09-03 2003-12-20 Андреев Анатолий Васильевич Камера сгорания
US6840048B2 (en) * 2002-09-26 2005-01-11 General Electric Company Dynamically uncoupled can combustor
US7334408B2 (en) * 2004-09-21 2008-02-26 Siemens Aktiengesellschaft Combustion chamber for a gas turbine with at least two resonator devices
EP1722069A1 (en) * 2005-05-13 2006-11-15 Siemens Aktiengesellschaft Combustion turbine engine
FR2905734B1 (fr) * 2006-09-07 2012-07-13 Airbus France Dispositif permettant d'ameliorer l'efficacite des traitements acoustiques dans un conduit d'une motorisation d'aeronef
US9822649B2 (en) * 2008-11-12 2017-11-21 General Electric Company Integrated combustor and stage 1 nozzle in a gas turbine and method
JP5180807B2 (ja) * 2008-12-24 2013-04-10 三菱重工業株式会社 １段静翼の冷却構造、及びガスタービン
US8408004B2 (en) 2009-06-16 2013-04-02 General Electric Company Resonator assembly for mitigating dynamics in gas turbines
JP5479058B2 (ja) * 2009-12-07 2014-04-23 三菱重工業株式会社 燃焼器とタービン部との連通構造、および、ガスタービン
US10030872B2 (en) * 2011-02-28 2018-07-24 General Electric Company Combustor mixing joint with flow disruption surface
JP5647039B2 (ja) 2011-03-11 2014-12-24 三菱重工業株式会社 ガスタービン
US20140013754A1 (en) * 2011-03-31 2014-01-16 Ilya Aleksandrovich Slobodyanskiy Power augmentation system with dynamics damping
CH704829A2 (de) 2011-04-08 2012-11-15 Alstom Technology Ltd Gasturbogruppe und zugehöriges Betriebsverfahren.

Also Published As

Publication number Publication date
CN103775213B (zh) 2017-01-04
JP2014085107A (ja) 2014-05-12
CA2830690C (en) 2016-02-23
JP5726267B2 (ja) 2015-05-27
KR20140052873A (ko) 2014-05-07
US20140109578A1 (en) 2014-04-24
EP2725198A1 (en) 2014-04-30
KR101576457B1 (ko) 2015-12-21
EP2725198B1 (en) 2017-09-20
US9429032B2 (en) 2016-08-30
RU2013147337A (ru) 2015-04-27
RU2552886C2 (ru) 2015-06-10
CN103775213A (zh) 2014-05-07
CA2830690A1 (en) 2014-04-24
EP2725196A1 (en) 2014-04-30

Similar Documents

Publication Publication Date Title
SA113340953B1 (ar) ناقل للاحتراق متكيف ليوجه غازات الاحتراق في ممر تدفق غاز ساخن
SA113340952B1 (ar) ناقل للاحتراق متكيف ليوجه غازات الاحتراق في ممر تدفق غاز ساخن
WO2014099077A3 (en) Gas turbine engine asymmetric nozzle guide vanes
WO2009041436A1 (ja) ガスタービン燃焼器
WO2010019175A3 (en) Transition duct for gas turbine combustor with inlet and outlet circumferentially offset
WO2010019177A3 (en) Transition with a linear flow path with exhaust mouths for use in a gas turbine engine
AU2013337647A8 (en) System and method for load control with diffusion combustion in a stoichiometric exhaust gas recirculation gas turbine system
MX2013010930A (es) Montaje de turbina de gas y el metodo de operacion correspondiente.
GB201303700D0 (en) Rotating turbomachine component having a tip leakage flow guide
WO2014114653A3 (en) Gas turbine outer case active ambient cooling including air exhaust into sub-ambient cavity
RU2011103223A (ru) Система, содержащая топливное сопло, система, содержащая турбинное топливное сопло, и система, содержащая турбинный двигатель
WO2013165507A3 (en) Cooling hole with asymmetric diffuser
EP2532968A3 (en) Integrated late lean injection on a combustion liner and late lean injection sleeve assembly
MY166869A (en) Combustion burner, solid-fuel-combustion burner, solid-fuel-combustion boiler, boiler, and method for operating boiler
WO2014077922A3 (en) Nacelle scoop inlet
EP2574844A3 (en) System for supplying pressured fluid to a cap assembly of a gas turbine combustor
WO2013143983A3 (en) Mixing arrangement for mixing a fuel with a stream of oxygen containing gas
GB201115043D0 (en) Steam injected gas turbine engine
WO2014099074A3 (en) Gas turbine engine combustor with integrated combustor vane
SA113340804B1 (ar) طريقة لمزج هواء مخفف في نظام احتراق تسلسلي لتربينة غازية
WO2013122643A3 (en) Device to lower nox in a gas turbine engine combustion system
EP4438857A3 (en) Low turn flow loss baffle for a gas turbine
WO2014099097A3 (en) Combustor seal mistake-proofing for a gas turbine engine
UA107163C2 (xx) Повітронагрівник з верхнім обігрівом
EP2778533A3 (en) Combustor for gas turbine engine