EP0014941A1 - Enveloppe refroidie pour turbine ou compresseur - Google Patents

Enveloppe refroidie pour turbine ou compresseur Download PDF

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Publication number
EP0014941A1
EP0014941A1 EP80100699A EP80100699A EP0014941A1 EP 0014941 A1 EP0014941 A1 EP 0014941A1 EP 80100699 A EP80100699 A EP 80100699A EP 80100699 A EP80100699 A EP 80100699A EP 0014941 A1 EP0014941 A1 EP 0014941A1
Authority
EP
European Patent Office
Prior art keywords
cooling gas
housing
jacket
inlet
cooled turbine
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
EP80100699A
Other languages
German (de)
English (en)
Other versions
EP0014941B1 (fr
Inventor
Hartmut Dr. Dipl.-Ing. Griepentrog
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.)
Gutehoffnungshutte Sterkrade AG
Original Assignee
Gutehoffnungshutte Sterkrade 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 Gutehoffnungshutte Sterkrade AG filed Critical Gutehoffnungshutte Sterkrade AG
Publication of EP0014941A1 publication Critical patent/EP0014941A1/fr
Application granted granted Critical
Publication of EP0014941B1 publication Critical patent/EP0014941B1/fr
Expired 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
    • F01D25/14—Casings modified therefor
    • 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
    • F01D25/14—Casings modified therefor
    • F01D25/145—Thermally insulated casings

Definitions

  • the invention relates to a cooled turbine or compressor housing, which is surrounded by a jacket, wherein the space between the jacket and the flow machine housing is flowed through by a cooling gas separated from the working medium and the cooling gas inlet and outlet openings open into the environment.
  • Such a housing is described in CH-PS 210 654.
  • the document shows and describes a gas turbine in which the turbine housing is flowed through by a gaseous coolant which enters and exits through relatively small openings, so that obviously additional conveying devices have to be provided.
  • the direction of flow seen from the drawing of the aforementioned CH-PS also allows this conclusion.
  • the additional conveying devices also increase the cost and susceptibility of the turbine or the compressor to malfunction.
  • the housing according to the invention must also enable cooling in process gas turbines which are designed for operation with gases with temperatures higher than 700 ° C. Insulations which are applied directly to the outside of the housing are not suitable, particularly with these turbines, since they do not enable the necessary temperature reduction in the housing wall. The creep rupture strength is therefore not sufficiently guaranteed.
  • Cooling channels are formed in the space between the jacket and the fluid machine housing.
  • the cooling channels and their inlets and outlets are distributed and dimensioned such that a sufficient, natural convection flow can develop due to the thermal buoyancy.
  • the housing according to the invention should therefore at least in the foot - or apex area have inlet and outlet openings for the cooling passages.
  • a turbine housing 100 is shown in the figure. It is easily possible to transfer the inventive idea to a compressor housing, since the problem of temperature dissipation is the same for the two types of housing.
  • the housing 100 shown in the sections according to FIGS. 1 and 2 consists of an upper shell 1 and a lower shell 2.
  • the resulting housing 100 has an essentially uniform, egg-shaped shape.
  • the upper shell 1 is equipped with connecting pieces 3, 4 projecting upward from the housing, the arrows showing the flow directions showing the inlet and outlet ports.
  • the housing consisting of the shells 1 and 2 is surrounded by an insulating jacket 5, which consists, for example, of pressed rock wool or high-temperature resistant SiO 2 or A1 2 0 3 fibers.
  • ribs, steel beams or the like are attached to the outside of the actual housing or to the connecting piece, which reach through the insulating jacket and fasten it. Such fastening ribs 6 are shown in FIG.
  • Through the jacket 5 also extend the input and output shafts 19 ', 19 ", which are indicated by dashed lines in the drawing.
  • a space is formed between the insulating jacket 5 and the housing and connecting piece walls 7, which serves as a cooling channel 8, which thus extends practically over the entire surface of the housing shells 1, 2.
  • cooling gas openings 14 are also provided for the cooling channels in the central region, namely on the all-round joint on the longitudinal flanges between the upper and lower shell, the outside air flowing in there mixes with the convection air flow, amplifies and cools it. This improves heat dissipation.
  • the cooling ducts are arranged in the area of the upper shell in such a way that they also extend along the connection pipe shell 13 and have an outlet opening 10 in the area of the pipe flange 11.
  • inlet and outlet openings for the intermediate space is selected in such a way that a path with as little air resistance as possible is provided for the ascending cooling gases.
  • inlet and outlet openings are all around in the area of the joint 9, d. H. in the axis plane, and in the foot area of the housing (at 12).
  • a turbine housing can also be designed in such a way that main connecting pieces are present at the top and bottom.
  • the cooling channels and insulating jacket of the lower shell are arranged in mirror image to that of the upper shell.
  • the inlet temperature in the inlet connection 3 is 727 ° C.
  • it is, for example, in the outlet connection 620 ° C.
  • Temperatures occur in the interior of the housing, which are approximately between 400 ° C. and 700 ° C. It is plausible that when the insulating jacket rests directly on the outer wall of the housing, the resulting amounts of heat cannot be dissipated to a sufficient extent, so that the housing can overheat and thus shorten the stability of the turbine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP19800100699 1979-02-14 1980-02-12 Enveloppe refroidie pour turbine ou compresseur Expired EP0014941B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19792905564 DE2905564C2 (de) 1979-02-14 1979-02-14 Gekühltes Turbinen- oder Verdichtergehäuse
DE2905564 1979-02-14

Publications (2)

Publication Number Publication Date
EP0014941A1 true EP0014941A1 (fr) 1980-09-03
EP0014941B1 EP0014941B1 (fr) 1982-03-31

Family

ID=6062875

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19800100699 Expired EP0014941B1 (fr) 1979-02-14 1980-02-12 Enveloppe refroidie pour turbine ou compresseur

Country Status (5)

Country Link
EP (1) EP0014941B1 (fr)
JP (2) JPS55109705A (fr)
BR (1) BR8000882A (fr)
DE (1) DE2905564C2 (fr)
MX (1) MX149954A (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000011324A1 (fr) * 1998-08-18 2000-03-02 Siemens Aktiengesellschaft Carter de turbine
WO2003038242A1 (fr) * 2001-10-30 2003-05-08 Alstom Technology Ltd Turbomachine
US7451598B2 (en) * 2002-09-25 2008-11-18 Dbt Australia Pty Limited Turbocharged compression ignition engine
EP2065568A1 (fr) * 2007-11-28 2009-06-03 Siemens Aktiengesellschaft Refroidissement d'une turbine à vapeur
WO2016010847A1 (fr) * 2014-07-16 2016-01-21 Borgwarner Inc. Turbocompresseur à gaz d'échappement à enveloppe thermiquement isolée
CN109057887A (zh) * 2018-09-25 2018-12-21 西安热工研究院有限公司 超临界工质透平壳体保温及内外对流冷却装置及其工作方法
CN109083704A (zh) * 2018-09-25 2018-12-25 西安热工研究院有限公司 超临界工质涡轮机组壳体保温散热装置及方法

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2230196C1 (ru) * 2002-12-06 2004-06-10 Акционерное общество открытого типа "Невский завод" Способ защиты от перегрева корпусных деталей газовой турбины и устройство для его осуществления

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE367109C (de) * 1922-02-28 1923-01-17 Michael Knoerlein Dipl Ing Luftkuehlung von Verbrennungskraftmaschinen, insbesondere Turbinen
DE507129C (de) * 1927-11-27 1930-09-12 Bbc Brown Boveri & Cie Einrichtung zum Ausgleich der Waerme waehrend des Erkaltens einer ausser Betrieb gesetzten Dampf- oder Gasturbine
CH210654A (de) * 1937-07-07 1940-07-31 Es Ertek Talalmanykifejlesztoe Gasturbine.
CH214696A (de) * 1939-12-27 1941-05-15 Maschf Augsburg Nuernberg Ag Gasturbinenanlage.
CH245486A (de) * 1944-12-22 1946-11-15 Oerlikon Maschf Verfahren zur Kühlung von Teilen einer Wärmekraftanlage.
CH271215A (de) * 1950-04-28 1950-10-15 Huldr Schneebeli Jac Gasturbinenanlage.
CH425341A (de) * 1965-07-23 1966-11-30 Bbc Brown Boveri & Cie Gasturbine mit Kühlung der Schaufelträger

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1034924B (de) * 1953-08-21 1958-07-24 Sulzer Ag Gasturbine mit verripptem Gehaeuse
JPS545921Y2 (fr) * 1975-06-16 1979-03-17

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE367109C (de) * 1922-02-28 1923-01-17 Michael Knoerlein Dipl Ing Luftkuehlung von Verbrennungskraftmaschinen, insbesondere Turbinen
DE507129C (de) * 1927-11-27 1930-09-12 Bbc Brown Boveri & Cie Einrichtung zum Ausgleich der Waerme waehrend des Erkaltens einer ausser Betrieb gesetzten Dampf- oder Gasturbine
CH210654A (de) * 1937-07-07 1940-07-31 Es Ertek Talalmanykifejlesztoe Gasturbine.
CH214696A (de) * 1939-12-27 1941-05-15 Maschf Augsburg Nuernberg Ag Gasturbinenanlage.
CH245486A (de) * 1944-12-22 1946-11-15 Oerlikon Maschf Verfahren zur Kühlung von Teilen einer Wärmekraftanlage.
CH271215A (de) * 1950-04-28 1950-10-15 Huldr Schneebeli Jac Gasturbinenanlage.
CH425341A (de) * 1965-07-23 1966-11-30 Bbc Brown Boveri & Cie Gasturbine mit Kühlung der Schaufelträger

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000011324A1 (fr) * 1998-08-18 2000-03-02 Siemens Aktiengesellschaft Carter de turbine
US6478534B2 (en) 1998-08-18 2002-11-12 Siemnes Aktiengesellschaft Turbine casing
CN1119511C (zh) * 1998-08-18 2003-08-27 西门子公司 透平机壳体和避免其在关停透平机后发生弯曲变形的方法
WO2003038242A1 (fr) * 2001-10-30 2003-05-08 Alstom Technology Ltd Turbomachine
US6978622B2 (en) 2001-10-30 2005-12-27 Alstom Technology Ltd Turbomachine
US7451598B2 (en) * 2002-09-25 2008-11-18 Dbt Australia Pty Limited Turbocharged compression ignition engine
EP2065568A1 (fr) * 2007-11-28 2009-06-03 Siemens Aktiengesellschaft Refroidissement d'une turbine à vapeur
WO2016010847A1 (fr) * 2014-07-16 2016-01-21 Borgwarner Inc. Turbocompresseur à gaz d'échappement à enveloppe thermiquement isolée
CN109057887A (zh) * 2018-09-25 2018-12-21 西安热工研究院有限公司 超临界工质透平壳体保温及内外对流冷却装置及其工作方法
CN109083704A (zh) * 2018-09-25 2018-12-25 西安热工研究院有限公司 超临界工质涡轮机组壳体保温散热装置及方法
CN109083704B (zh) * 2018-09-25 2023-10-20 西安热工研究院有限公司 超临界工质涡轮机组壳体保温散热装置及方法
CN109057887B (zh) * 2018-09-25 2023-12-12 西安热工研究院有限公司 超临界工质透平壳体保温及内外对流冷却装置及其工作方法

Also Published As

Publication number Publication date
EP0014941B1 (fr) 1982-03-31
DE2905564B1 (de) 1981-01-29
MX149954A (es) 1984-02-15
JPS6351102U (fr) 1988-04-06
JPH0329522Y2 (fr) 1991-06-24
BR8000882A (pt) 1980-10-21
DE2905564C2 (de) 1981-08-27
JPS55109705A (en) 1980-08-23

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