EP1170464A2 - Dispositif de refroidissement d'un élément avec une charge thermique inégale - Google Patents

Dispositif de refroidissement d'un élément avec une charge thermique inégale Download PDF

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Publication number
EP1170464A2
EP1170464A2 EP01113867A EP01113867A EP1170464A2 EP 1170464 A2 EP1170464 A2 EP 1170464A2 EP 01113867 A EP01113867 A EP 01113867A EP 01113867 A EP01113867 A EP 01113867A EP 1170464 A2 EP1170464 A2 EP 1170464A2
Authority
EP
European Patent Office
Prior art keywords
component
ring
slots
cooling air
sections
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.)
Granted
Application number
EP01113867A
Other languages
German (de)
English (en)
Other versions
EP1170464A3 (fr
EP1170464B1 (fr
Inventor
Emil Aschenruck
Hildegard Ebbing
Klaus Dieter Mohr
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.)
MAN Energy Solutions SE
Original Assignee
MAN Turbomaschinen AG GHH Borsig
MAN Turbomaschinen 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 MAN Turbomaschinen AG GHH Borsig, MAN Turbomaschinen AG filed Critical MAN Turbomaschinen AG GHH Borsig
Publication of EP1170464A2 publication Critical patent/EP1170464A2/fr
Publication of EP1170464A3 publication Critical patent/EP1170464A3/fr
Application granted granted Critical
Publication of EP1170464B1 publication Critical patent/EP1170464B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • 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
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid

Definitions

  • the invention relates to a device for cooling a symmetrical, due to high temperatures over the circumference component of a turbine system subjected to unevenly heavy loads with the features of the preamble of claim 1.
  • Such components are at different points in gas and steam turbine systems are provided.
  • a special The application is the two-armed, with two inlet sockets Provided gas manifold, also called downpipe, the in Gas turbine plants between the combustion chamber housings and the The inlet nozzle of the turbine blades is arranged (DE-OS 198 15 473). Due to the special shape of the inlet nozzle this gas manifold are in its outlet cross section middle areas are much more thermally stressed than the upper and lower area.
  • the outlet cross-section is cooled by cooling air is guided along the side facing away from the hot gas.
  • This Cooling air is taken from the compressor of the gas turbine system.
  • the Amount of cooling air limited by slots in the annular inner flange of the gas collecting tube are arranged, which is connected to the counter flange of the turbine. This Slots are even in the known gas turbine system distributed over the circumference of the inner flange. by virtue of the asymmetrical application of temperature by the of the hot gas flows coming in both combustion chambers in combination with the symmetrical cooling air distribution results in Circumferential direction on the inner flange of the gas manifold uneven material temperature.
  • the invention has for its object the cooling of non-uniformly thermally stressed, generic components to equalize without additional effort.
  • the intensity of convection cooling by the cooling air in the Exit cross section is determined by the speed and the amount of cooling air that flows along there. With that at all Cooling air flows, there is a pressure difference ⁇ p above that slotted annular inner flange required.
  • the Cooling air flows through the circumference of the inner flange arranged slots.
  • the ring-shaped inner flange of the component thus represents Throttle body for the amount of cooling air.
  • Cooling air that normally cools areas that are low Temperature exposure have led to the areas that are exposed to higher temperatures.
  • This increases the Material temperature of the outlet cross section in the cold Zones.
  • the temperatures drop in the two hot ones Zones so that considered on the perimeter. an almost gives a uniform temperature profile.
  • the resulting from the measures according to the invention are a reduction in local, life-limiting material temperature, in one Uniformization of the temperature distribution, in a reduction of temperature tensions, in an improvement in temperature and corrosion resistance and in an increase in Component life.
  • Another advantage is that no increased Cooling air required. With the previously known and methods used to meet temperature peaks in Components that are subject to high temperatures are usually the additional cooling air is supplied to hot zones. This additional Cooling air is usually not available, however, or it leads to a reduction in the efficiency of the machine.
  • the component shown as an example in the drawing is a Hot gas leading two-armed gas manifold 1, the inside a gas turbine plant between those not shown Combustion chamber housings and the inlet port of the not shown Turbine blades are arranged.
  • the gas manifold 1 is with two inlet ports 2 for the hot gas from the combustion chambers Mistake.
  • the inlet ports open into a gas collecting space 3 in lower part of the gas collecting tube 1.
  • the gas manifold 1 is with an outer ring flange 4 and an inner ring flange 5 provided, which are connected to the counter flanges of the gas turbine become.
  • the compressed hot gas flows out of the combustion chambers through the inlet nozzle 2 of the gas manifold 1 and is in the gas plenum 3 merged and collected before being in the gas turbine flows and the turbine rotor with the Rotating blades.
  • the inlet nozzle 2 Due to the design of the inlet nozzle 2 is the Gas collecting chamber 3 of the two-armed gas collecting tube 1 through the introduced hot gas unevenly thermally loaded. There are the middle areas, the 3 o'clock and 9 o'clock positions correspond, more heavily burdened than the upper and the lower area of the gas collecting space 3 according to the 6 o'clock and the 12 o'clock position.
  • the entire gas collecting tube 1 is outside by compressor air convectively cooled, the compressor of the gas turbine plant is removed.
  • This cooling air is used on the Inner cone 6 of the gas collecting space 3 is guided along.
  • To this Purpose are in the inner ring flange 5, which as a ring in the Flow path of the cooling air protrudes, slots 7 or others Openings attached.
  • the cooling air flows through these slots 7 from.
  • the driving force for the flow of cooling air is one Pressure difference, which is on both sides of the slotted inner ring flange 5 builds.
  • the slots 7 are uneven in the inner ring flange 5 distributed over its circumference. As from Fig. 2 too can be seen, the distance of the slots 7 from each other in the Sections of the inner ring flange 5 largest, the most strongest thermally stressed areas of the gas collecting space 3 are neighboring. These are the areas that the 3 o'clock and the Correspond to 9 o'clock position. In those sections of the inner ring flange 5, which the least heavily loaded Regions of the gas collecting space 3 are adjacent, the distance the slots 7 from each other largest. Based on these Distribution of the slots 7, the cooling air flows along increasingly the most thermally stressed areas of the Gas collection room 3.
  • the width of the slots 7 in the Ways can be varied so that the slots 7 over the circumference of the Ring flange 5 have a different width and that the width of the slots 7 in the sections of the ring flange 5th is larger, the more heavily used areas of the Gas collecting tube 1 are adjacent.
  • the slots 7 of different widths evenly or as before for the slots 7 of equal width is explained, unevenly over the The circumference of the inner ring flange 5 can be distributed.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Crushing And Grinding (AREA)
  • Thermotherapy And Cooling Therapy Devices (AREA)
EP01113867A 2000-07-04 2001-06-07 Dispositif de refroidissement d'un élément avec une charge thermique inégale Expired - Lifetime EP1170464B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10032454A DE10032454A1 (de) 2000-07-04 2000-07-04 Vorrichtung zum Kühlen eines ungleichmäßig stark temperaturbelasteten Bauteiles
DE10032454 2000-07-04

Publications (3)

Publication Number Publication Date
EP1170464A2 true EP1170464A2 (fr) 2002-01-09
EP1170464A3 EP1170464A3 (fr) 2003-07-02
EP1170464B1 EP1170464B1 (fr) 2006-03-15

Family

ID=7647737

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01113867A Expired - Lifetime EP1170464B1 (fr) 2000-07-04 2001-06-07 Dispositif de refroidissement d'un élément avec une charge thermique inégale

Country Status (4)

Country Link
US (1) US6568902B2 (fr)
EP (1) EP1170464B1 (fr)
AT (1) ATE320547T1 (fr)
DE (2) DE10032454A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016078984A1 (fr) * 2014-11-20 2016-05-26 Siemens Aktiengesellschaft Profil d'admission pour dispositif à un seul corps
WO2016173920A1 (fr) * 2015-04-28 2016-11-03 Siemens Aktiengesellschaft Carter guidant des gaz chauds

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10239534A1 (de) * 2002-08-23 2004-04-22 Man Turbomaschinen Ag Heißgas führendes Gassammelrohr
USD818502S1 (en) * 2015-12-17 2018-05-22 General Electric Company Turbocharger transition section
JP6578203B2 (ja) * 2015-12-24 2019-09-18 三菱日立パワーシステムズ株式会社 蒸気タービン冷却装置
USD814522S1 (en) * 2016-06-21 2018-04-03 General Electric Company Transition section for a turbocharged engine

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2402841A (en) * 1944-06-26 1946-06-25 Allis Chalmers Mfg Co Elastic fluid turbine apparatus
GB580042A (en) * 1944-01-21 1946-08-26 Dehavilland Aircraft Improvements in or relating to turbo-compressor propulsive apparatus
US2608057A (en) * 1949-12-24 1952-08-26 A V Roe Canada Ltd Gas turbine nozzle box
US3670497A (en) * 1970-09-02 1972-06-20 United Aircraft Corp Combustion chamber support
US4841726A (en) * 1985-11-19 1989-06-27 Mtu-Munchen Gmbh Gas turbine jet engine of multi-shaft double-flow construction
EP0492865A1 (fr) * 1990-12-21 1992-07-01 General Electric Company Système de régulation pour le jeu des extrémités des aubes de turbine
DE19815473A1 (de) * 1998-04-07 1999-10-14 Ghh Borsig Turbomaschinen Gmbh Heißgasführendes Gassammelrohr einer Gasturbine
EP1146289A1 (fr) * 2000-04-13 2001-10-17 Mitsubishi Heavy Industries, Ltd. Réfroidissement de la partie aval d'une chambre de combustion

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4329114A (en) 1979-07-25 1982-05-11 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Active clearance control system for a turbomachine
FR2652858B1 (fr) * 1989-10-11 1993-05-07 Snecma Stator de turbomachine associe a des moyens de deformation.
DE4328401A1 (de) * 1993-08-24 1995-03-02 Abb Management Ag Turbinenschaufel für eine Gasturbine

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB580042A (en) * 1944-01-21 1946-08-26 Dehavilland Aircraft Improvements in or relating to turbo-compressor propulsive apparatus
US2402841A (en) * 1944-06-26 1946-06-25 Allis Chalmers Mfg Co Elastic fluid turbine apparatus
US2608057A (en) * 1949-12-24 1952-08-26 A V Roe Canada Ltd Gas turbine nozzle box
US3670497A (en) * 1970-09-02 1972-06-20 United Aircraft Corp Combustion chamber support
US4841726A (en) * 1985-11-19 1989-06-27 Mtu-Munchen Gmbh Gas turbine jet engine of multi-shaft double-flow construction
EP0492865A1 (fr) * 1990-12-21 1992-07-01 General Electric Company Système de régulation pour le jeu des extrémités des aubes de turbine
DE19815473A1 (de) * 1998-04-07 1999-10-14 Ghh Borsig Turbomaschinen Gmbh Heißgasführendes Gassammelrohr einer Gasturbine
EP1146289A1 (fr) * 2000-04-13 2001-10-17 Mitsubishi Heavy Industries, Ltd. Réfroidissement de la partie aval d'une chambre de combustion

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016078984A1 (fr) * 2014-11-20 2016-05-26 Siemens Aktiengesellschaft Profil d'admission pour dispositif à un seul corps
CN107075962A (zh) * 2014-11-20 2017-08-18 西门子公司 用于单轴装置的入流轮廓部
CN107075962B (zh) * 2014-11-20 2019-07-09 西门子公司 用于单轴装置的入流轮廓部
US10533438B2 (en) 2014-11-20 2020-01-14 Siemens Aktiengesellschaft Inflow contour for a single-shaft arrangement
WO2016173920A1 (fr) * 2015-04-28 2016-11-03 Siemens Aktiengesellschaft Carter guidant des gaz chauds

Also Published As

Publication number Publication date
US20020004003A1 (en) 2002-01-10
DE10032454A1 (de) 2002-01-17
ATE320547T1 (de) 2006-04-15
US6568902B2 (en) 2003-05-27
EP1170464A3 (fr) 2003-07-02
EP1170464B1 (fr) 2006-03-15
DE50109194D1 (de) 2006-05-11

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