EP0040267A1 - Stator refroidi pour turbines - Google Patents

Stator refroidi pour turbines Download PDF

Info

Publication number
EP0040267A1
EP0040267A1 EP80200461A EP80200461A EP0040267A1 EP 0040267 A1 EP0040267 A1 EP 0040267A1 EP 80200461 A EP80200461 A EP 80200461A EP 80200461 A EP80200461 A EP 80200461A EP 0040267 A1 EP0040267 A1 EP 0040267A1
Authority
EP
European Patent Office
Prior art keywords
guide vane
vane carrier
carrier according
guide
channels
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
EP80200461A
Other languages
German (de)
English (en)
Other versions
EP0040267B1 (fr
Inventor
Wolfgang Beckershoff
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.)
BBC Brown Boveri AG Switzerland
Original Assignee
BBC Brown Boveri AG Switzerland
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 BBC Brown Boveri AG Switzerland filed Critical BBC Brown Boveri AG Switzerland
Priority to AT80200461T priority Critical patent/ATE16035T1/de
Priority to DE8080200461T priority patent/DE3071161D1/de
Priority to EP80200461A priority patent/EP0040267B1/fr
Priority to JP6351181A priority patent/JPS5710707A/ja
Priority to US06/260,336 priority patent/US4386885A/en
Publication of EP0040267A1 publication Critical patent/EP0040267A1/fr
Application granted granted Critical
Publication of EP0040267B1 publication Critical patent/EP0040267B1/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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • 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

Definitions

  • the present invention relates to a guide vane carrier for a gas turbine, which is designed in two parts and is provided with cooling channels and carries cooled guide vanes and is conical in relation to the longitudinal axis of the turbine.
  • the guide vane carriers in gas turbines take on the Guide vanes acting aerodynamic forces and forward them to the housing, whereby the guide vane carriers are exposed to the typical boiler tensions as the machine housing at a relatively high intrinsic temperature.
  • guide vane supports were formed as separate parts, which made it possible for them to expand freely due to their own temperature. They are arranged housing in known manner in the overall 'that they are advantageously fixed in the downstream cooler parts and sealed.
  • the conical design of the guide vane carrier enables the arrangement of coolant channels in its walls, the curvature and kink-free design of its longitudinal section profile reducing the bending moment on the partial flange due to residual thermal stresses in the wall to a minimum.
  • the tapping holes branching off from the coolant channels to the individual guide vanes enable a uniform and adjustable coolant flow.
  • the arrangement according to the invention of preferably obliquely axial bores or channels in the wall line of gravity avoids expansion differences which can lead to bending moments and the resulting flange stresses.
  • the design of the coolant guides as oblique-axial channels or pipes cast into the guide vane carrier wall, which alternately have coolant supply lines and discharge lines over the circumference of the guide vane carrier, with radial or radial-axial feed bores from or to the components to be cooled being arranged at suitable locations can, by means of this arrangement alternating over the circumference in the wall, on average compensate for the locally different temperature influences.
  • the arrangement of the coolant channels in the neutral phase of the guide vane carrier wall results in the advantages that the inevitable weakening of the guide vane carrier wall when bending moments and tensile forces occur, and for other uneven temperature distributions due to different residual wall thicknesses and resulting deformations can be avoided.
  • the arrangement of a cylindrically shaped part on the high-pressure side end of the guide vane carrier simplifies the fastening of the components to be connected at this end, for example the inlet segments, the hot gas housing and the intermediate jacket.
  • the guide vane carriers preferably have a separating surface in the horizontal plane, a partial surface screw connection must be provided, which must be designed in such a way that it does not diverge during operation as a result of the bending moments that occur as a result of thermal stresses.
  • the inventive comb profile-like design of the flange screw connection of the guide vane carrier wherein the comb profiles can be formed by welding individual sheets, enables the partial surface flange to be screwed together by means of screws which are located in slots which are open on one side.
  • the flange material delimiting the screw slots forms rib-like projections which, in connection with the. Wall of the guide vane carrier form the comb profile. Since each slot only has to have the width of the screw shaft, for example the expansion shaft of an expansion screw, the comb section can be kept much smaller.
  • the open slots of the air flowing around the guide vane carrier and coming out of the compressor allow these parts to flow freely, whereby both the flange material and the fastening screws are heated evenly, so that the otherwise usual thermal stresses in the flange zone and the expansion of the screw shafts beyond the yield point be avoided.
  • the section modulus and the overall cross-section are reinforced by the comb profiles, the slots can be made so deep that they affect the sealing strip provided.
  • the groove base of the slots is semicircular, whereby the notch effect is largely eliminated, which is particularly the case with Comb profiles welded together from sheet metal parts have an advantageous effect as a wall transition which is largely defused in terms of the notch effect, and the removal of the penetration which occurs during welding is facilitated.
  • the expansion bolts are held in nut supports, each of which bridges a slot, these nut supports with their preferred and formed boundary surface lying in a groove provided in parallel with the flange surface and having a semicircular cross section.
  • the outer contour of the comb-like flange plates advantageously runs almost rectilinearly and the comb part, which is based on a smooth wall, results in a thickness distribution in which, compared to the known flange contours, material accumulations are much smaller. This applies to both the cross-section itself and 'die existing moments of resistance. The rugged cross-sectional transitions are also missing in such a design.
  • the inlet sections can be locked in the axial direction, in such a way that massive projections of the inlet section engage behind resiliently resilient lugs on the guide vane carrier.
  • the connecting elements to the coolant channels are simultaneously brought into an elastic, form-fitting connection with the guide vane carrier.
  • 1 and 2 denotes a guide vane carrier which has a conically shaped section 2 and a cylindrical section 3, the conical section 2 having the same angle of inclination essentially over its entire length.
  • guide lugs 4 are arranged which guide the guide vane carrier 1 in the machine housing (not shown).
  • the guide lugs 4 'additionally serve to limit displacements of a hot gas housing 5 with an intermediate jacket 6 and a rib 7 is used as a spacer between these two components 10 is arranged in the cylindrical portion 3 and in a nose 11 of a locking element 12. Hollow inlet segments 13 are also attached to the locking element 12.
  • the locking element 12 also serves to guide and seal the connection of the hot gas housing 5, as well as to guide the intermediate jacket 6 and a cooling medium passage 14 for introducing the inlet segment cooling medium, the holder of the inlet segments 13, the holder of the first guide vane / row 10 5 and the guide of cooling medium connecting elements 15, which are arranged between the cooling medium passage 14 and the cooling channel system of the inlet segments 13.
  • Cooling channels 16 are arranged in the guide vane carrier 1 and are supplied with coolant via inlet openings 17 or from which the heated coolant flows out via outlet openings 18.
  • the inlet openings 17 and outlet openings 18 are arranged alternately lying next to one another over the circumference (see also FIGS. 4 and 5).
  • the cooling channels 16 are connected to the cooling channel system of the guide vanes 9, 10 via connecting channels 19. Between the connecting channels 19 and the inlet openings in the guide vanes 9, 10 there are sealing elements 20 provided with passages, which prevent cooling medium from escaping into the spaces between the guide vane feet 21.
  • the cooling channels 16 can be closed at the high-pressure end of the guide vane carrier 1 when no inlet segments 3 need to be cooled.
  • cooling channels 16 alternately supply the guide vanes 9, 10 alone and the inlet segments 13 with cooling medium alternately over the circumference of the guide vane carrier 1, the cooling channel 16 is therefore also alternately closed in pairs or is free to the coolant passage 14 .
  • the arrows drawn in FIGS. 1 and 2 show the direction of flow of the cooling medium.
  • the inlet segment 13 can be, for example, an end piece of an annular combustion chamber.
  • the cross section through the guide vane carrier 1 according to FIG. 4 illustrates the alternating arrangement of the supply and discharge lines of the cooling channels 16, 16 '.
  • two guide vanes 9 are fastened to a common base plate 22, distribution channels 29 being arranged in each base plate in such a way that they communicate with the connecting channels 19.
  • Comb profile-like screw connections 24 are provided in the partial surface area of the guide vane carrier 1.
  • the cylindrical section 3 of the guide vane carrier 1 has slots 25 which cancel out the stiffening effect of the kink between the conical section 2 and the cylindrical section 3, as well as the associated bending moments on the flange screw connection in the event of temperature differences.
  • FIGS. 6, 7 and 8 show details of the partial surface screw connection, again with 1 the wall of the guide vane carrier is designated, on which a flange 26 is arranged, which is tightened with fastening screws 27, preferably with expansion screws.
  • the flanges 26 are designed in such a way that the wall of the guide vane carrier 1 is designed in the manner of a comb profile in the region between the contact surfaces of the fastening screws 27, the slots (according to FIGS. 9 and 10) not being wider than the shaft diameter of the fastening screws 27 requires, while the remaining wall thickness of the guide vane carrier 1 is completely the same thickness is held.
  • the outer contour of the comb profiles 24 runs approximately in a straight line.
  • 27 nut supports 28 are provided under the nuts of the expansion screws, which have a cylindrical underside, which in turn is in a Corresponding grooves with a semicircular cross section is mounted on the flange, which at the same time form the notch-free transition from the flange combs to the general wall and secure the screws 27 together with nuts and nut supports 28 in the screwed state against slipping out of the slot 25 laterally. Since the cylindrical bearing surfaces permit rotary movements about their cylinder axes, this configuration is insensitive to an inclined position of the screws 27 and at least in one plane. thus the approval of coarser manufacturing tolerances.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Motor Or Generator Cooling System (AREA)
EP80200461A 1980-05-19 1980-05-19 Stator refroidi pour turbines Expired EP0040267B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
AT80200461T ATE16035T1 (de) 1980-05-19 1980-05-19 Gekuehlter leitschaufeltraeger.
DE8080200461T DE3071161D1 (en) 1980-05-19 1980-05-19 Cooled turbine stator
EP80200461A EP0040267B1 (fr) 1980-05-19 1980-05-19 Stator refroidi pour turbines
JP6351181A JPS5710707A (en) 1980-05-19 1981-04-28 Cooled guide blade holding body
US06/260,336 US4386885A (en) 1980-05-19 1981-05-04 Cooled guide support vane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP80200461A EP0040267B1 (fr) 1980-05-19 1980-05-19 Stator refroidi pour turbines

Publications (2)

Publication Number Publication Date
EP0040267A1 true EP0040267A1 (fr) 1981-11-25
EP0040267B1 EP0040267B1 (fr) 1985-10-09

Family

ID=8186999

Family Applications (1)

Application Number Title Priority Date Filing Date
EP80200461A Expired EP0040267B1 (fr) 1980-05-19 1980-05-19 Stator refroidi pour turbines

Country Status (5)

Country Link
US (1) US4386885A (fr)
EP (1) EP0040267B1 (fr)
JP (1) JPS5710707A (fr)
AT (1) ATE16035T1 (fr)
DE (1) DE3071161D1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0716159A1 (fr) 1994-12-07 1996-06-12 General Electric Company Articles aptes au brasage
EP0735243A2 (fr) * 1995-03-31 1996-10-02 General Electric Company Boîtier intérieur de turbine permettant la régulation du jeu entre les aubes et le boîtier
DE19546722A1 (de) * 1995-12-14 1997-06-19 Asea Brown Boveri Leitschaufelträger für eine Gasturbine
GB2327466A (en) * 1997-03-20 1999-01-27 Snecma A stator for a gas turbine compressor
EP2159384A1 (fr) * 2008-08-27 2010-03-03 Siemens Aktiengesellschaft Support statorique d'aubes directrices pour une turbine à gaz
FR3101105A1 (fr) * 2019-09-23 2021-03-26 Safran Aircraft Engines Carter pour turbomachine et turbomachine équipée d’un tel carter

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4627233A (en) * 1983-08-01 1986-12-09 United Technologies Corporation Stator assembly for bounding the working medium flow path of a gas turbine engine
JPS61173284U (fr) * 1985-04-15 1986-10-28
JPS62157377U (fr) * 1986-03-26 1987-10-06
US4907946A (en) * 1988-08-10 1990-03-13 General Electric Company Resiliently mounted outlet guide vane
DE4327376A1 (de) * 1993-08-14 1995-02-16 Abb Management Ag Verdichter sowie Verfahren zu dessen Betrieb
PL330755A1 (en) * 1996-06-21 1999-05-24 Siemens Ag Turbine shaft as well as method of cooling same
DE19643716A1 (de) 1996-10-23 1998-04-30 Asea Brown Boveri Schaufelträger für einen Verdichter
WO1998058158A1 (fr) * 1997-06-19 1998-12-23 Mitsubishi Heavy Industries, Ltd. Dispositif d'etancheite pour aubes de stator de turbine a gaz
GB0403198D0 (en) * 2004-02-13 2004-03-17 Rolls Royce Plc Casing arrangement
EP2148045A1 (fr) * 2008-07-25 2010-01-27 Siemens Aktiengesellschaft Section de boîtier pour une turbine à gaz
EP2159381A1 (fr) * 2008-08-27 2010-03-03 Siemens Aktiengesellschaft Support d'aube directrice de turbine pour une turbine à gaz

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE451857C (de) * 1925-01-06 1927-11-02 Bernhard Moll Dipl Ing Dampfkraftanlage, insbesondere Dampfturbine, mit Vorwaermung des Kesselspeisewassers
CH148852A (de) * 1930-07-08 1931-08-15 Escher Wyss Maschf Ag Dampf- oder Gasturbine, insbesondere für hohen Druck und hohe Temperatur.
US1938688A (en) * 1931-12-19 1933-12-12 Nanna S Brooke Gas turbine
CH202312A (de) * 1937-03-15 1939-01-15 Bbc Brown Boveri & Cie Einrichtung an mit Heissdampf betriebenen Maschinen zum raschen Anwärmen derselben.
GB510672A (en) * 1938-03-18 1939-08-04 British Thomson Houston Co Ltd Improvements in and relating to casings for elastic fluid turbines
GB675484A (en) * 1949-02-10 1952-07-09 English Electric Co Ltd Improvements in and relating to the stator cooling of gas turbines
US2618120A (en) * 1946-06-07 1952-11-18 Papini Anthony Coaxial combustion products generator and turbine with cooling means
CH425341A (de) * 1965-07-23 1966-11-30 Bbc Brown Boveri & Cie Gasturbine mit Kühlung der Schaufelträger
CH488098A (de) * 1968-04-10 1970-03-31 Licentia Gmbh Einrichtung zur Kühlung der Flansche an den Gehäuseteilfugen von Sattdampf- oder Nassdampfturbinen
DE1601845A1 (de) * 1967-07-12 1971-02-04 Escher Wyss Gmbh Verfahren zum Betreiben einer Dampf- oder Gasturbine mit von Arbeitsmittel durchstroemten Waermeaustauschkanaelen in Gehaeuseteilen groesserer Materialstaerke,sowie Dampf- oder Gasturbine zur Durchfuehung dieses Verfahrens

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2489683A (en) * 1943-11-19 1949-11-29 Edward A Stalker Turbine
US3275294A (en) * 1963-11-14 1966-09-27 Westinghouse Electric Corp Elastic fluid apparatus
GB1126469A (en) * 1964-09-24 1968-09-05 English Electric Co Ltd Improvements in or relating to gas turbines
US3734639A (en) * 1968-01-25 1973-05-22 Gen Motors Corp Turbine cooling
CH488931A (de) * 1968-03-22 1970-04-15 Sulzer Ag Gehäuse für Turbomaschinen, insbesondere axial getrenntes Gehäuse für Hochtemperaturturbinen
US3736069A (en) * 1968-10-28 1973-05-29 Gen Motors Corp Turbine stator cooling control
US4184689A (en) * 1978-10-02 1980-01-22 United Technologies Corporation Seal structure for an axial flow rotary machine

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE451857C (de) * 1925-01-06 1927-11-02 Bernhard Moll Dipl Ing Dampfkraftanlage, insbesondere Dampfturbine, mit Vorwaermung des Kesselspeisewassers
CH148852A (de) * 1930-07-08 1931-08-15 Escher Wyss Maschf Ag Dampf- oder Gasturbine, insbesondere für hohen Druck und hohe Temperatur.
US1938688A (en) * 1931-12-19 1933-12-12 Nanna S Brooke Gas turbine
CH202312A (de) * 1937-03-15 1939-01-15 Bbc Brown Boveri & Cie Einrichtung an mit Heissdampf betriebenen Maschinen zum raschen Anwärmen derselben.
GB510672A (en) * 1938-03-18 1939-08-04 British Thomson Houston Co Ltd Improvements in and relating to casings for elastic fluid turbines
US2618120A (en) * 1946-06-07 1952-11-18 Papini Anthony Coaxial combustion products generator and turbine with cooling means
GB675484A (en) * 1949-02-10 1952-07-09 English Electric Co Ltd Improvements in and relating to the stator cooling of gas turbines
CH425341A (de) * 1965-07-23 1966-11-30 Bbc Brown Boveri & Cie Gasturbine mit Kühlung der Schaufelträger
DE1601845A1 (de) * 1967-07-12 1971-02-04 Escher Wyss Gmbh Verfahren zum Betreiben einer Dampf- oder Gasturbine mit von Arbeitsmittel durchstroemten Waermeaustauschkanaelen in Gehaeuseteilen groesserer Materialstaerke,sowie Dampf- oder Gasturbine zur Durchfuehung dieses Verfahrens
CH488098A (de) * 1968-04-10 1970-03-31 Licentia Gmbh Einrichtung zur Kühlung der Flansche an den Gehäuseteilfugen von Sattdampf- oder Nassdampfturbinen

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0716159A1 (fr) 1994-12-07 1996-06-12 General Electric Company Articles aptes au brasage
EP0735243A2 (fr) * 1995-03-31 1996-10-02 General Electric Company Boîtier intérieur de turbine permettant la régulation du jeu entre les aubes et le boîtier
EP0735243A3 (fr) * 1995-03-31 1996-12-04 Gen Electric Boîtier intérieur de turbine permettant la régulation du jeu entre les aubes et le boîtier
US5913658A (en) * 1995-03-31 1999-06-22 General Electric Co. Removable inner turbine shell with bucket tip clearance control
US6079943A (en) * 1995-03-31 2000-06-27 General Electric Co. Removable inner turbine shell and bucket tip clearance control
US6082963A (en) * 1995-03-31 2000-07-04 General Electric Co. Removable inner turbine shell with bucket tip clearance control
DE19546722A1 (de) * 1995-12-14 1997-06-19 Asea Brown Boveri Leitschaufelträger für eine Gasturbine
DE19546722B4 (de) * 1995-12-14 2005-03-31 Alstom Leitschaufelträger für eine Gasturbine
GB2327466A (en) * 1997-03-20 1999-01-27 Snecma A stator for a gas turbine compressor
EP2159384A1 (fr) * 2008-08-27 2010-03-03 Siemens Aktiengesellschaft Support statorique d'aubes directrices pour une turbine à gaz
FR3101105A1 (fr) * 2019-09-23 2021-03-26 Safran Aircraft Engines Carter pour turbomachine et turbomachine équipée d’un tel carter

Also Published As

Publication number Publication date
JPS648173B2 (fr) 1989-02-13
ATE16035T1 (de) 1985-10-15
EP0040267B1 (fr) 1985-10-09
JPS5710707A (en) 1982-01-20
DE3071161D1 (en) 1985-11-14
US4386885A (en) 1983-06-07

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