EP0040267B1 - Stator refroidi pour turbines - Google Patents
Stator refroidi pour turbines Download PDFInfo
- Publication number
- EP0040267B1 EP0040267B1 EP80200461A EP80200461A EP0040267B1 EP 0040267 B1 EP0040267 B1 EP 0040267B1 EP 80200461 A EP80200461 A EP 80200461A EP 80200461 A EP80200461 A EP 80200461A EP 0040267 B1 EP0040267 B1 EP 0040267B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- guide vane
- vane carrier
- guide
- individual
- comb
- 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.)
- Expired
Links
Images
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 according to the preamble of the claim.
- the guide vane carriers in gas turbines take over the aerodynamic forces acting on the guide vanes and transmit them to the housing, the guide vane carriers being, however, not exposed to the typical boiler voltages as the machine housing at a relatively high intrinsic temperature.
- guide vane carriers were formed as separate parts, which made it possible for them to expand freely due to their own temperature. They are arranged in a known manner in the housing in such a way that they are advantageously fixed and sealed in the cooler parts lying downstream.
- a gas turbine of the type mentioned at the outset is known, for example, from US Pat. No. 2,618,120, in which the coolant is guided in cooling channels which are arranged in the circumferential direction and are used alternately as supply and discharge lines. These coolant channels are arranged on the surface, so that thermal stresses can occur in the individual shells of the guide vane carrier.
- the cooling air for the blade carrier is conducted in a channel, which is formed on the one hand by the inner wall of the blade carrier and on the other hand by an additionally inserted channel wall. After exiting the duct, the cooling air enters a duct which is closed by a casing and which covers part of the blade carrier (CH-A-425 341).
- a connection for the two halves of a guide vane carrier of a gas turbine has become known, in which tangential screwing elements are provided in the area of the parting plane of the two housing halves, which are supported on ribs-reinforced webs. These webs form abutments for the connecting bolts which have the same diameter over the entire length and which pass through eyes in the webs.
- This design of the connecting bolts requires relatively large distances between the individual connecting bolts, in which reinforcing ribs are arranged. With such a design, however, bending moments can occur from the thermal stresses that occur.
- the formation of the guide vane carrier with the tapping holes branching off from the coolant channels to the individual guide vanes enables a uniform and adjustable coolant flow, as a result of which the bending moment on the partial flange is reduced to a minimum as a result of residual heat stresses in the wall.
- 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 result from thermal stresses.
- the inventive comb profile-like design of the flange screw connection of the guide vane carrier 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 form the comb profile in connection with the wall of the guide vane carrier. Since each slot only needs to have the width of the screw shaft, for example the expansion shaft of an expansion screw, which has a much smaller diameter than the threaded parts thereof, the comb pitch 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, as a result of which 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. It can thus be achieved that the moment of inertia in the area of the flange corresponds to the moment of inertia over the entire circumference of the shell.
- the groove base of the slots is semicircular, which largely eliminates the notch effect, which has an advantageous effect, particularly in the case of comb profiles welded together from bleaching parts, as a wall transition which is largely defused with respect to 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 preferably round-shaped 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 in a straight line and the comb section, which is based on a smooth wall, results in a thickness distribution in which the material accumulations are considerably smaller than those of the known flange contours. This applies both to the cross section itself and to the 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 snap into the lugs arranged on the guide vane carrier.
- the connecting elements to the coolant channels are simultaneously brought into a positive connection with the guide vane carrier.
- 1 and 2, 1 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 serves 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 coolant 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, 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, which are charged with coolant via inlet openings 17, or from which the heated coolant flows out via outlet openings 18.
- the inlet 17 and outlet openings 18 are alternately adjacent to one another over the circumference arranged (see also Fig. 4 and 5).
- the cooling channels 16 are connected to the cooling channel system of the guide vanes 9, 10 via connecting channels 19.
- the cooling channels 16 can be closed at the high-pressure end of the guide vane carrier 1 when no inlet segments 13 need to be cooled. Since the 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 this is free for the passage of coolant 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 blades 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.
- FIGS. 1 to 4 From the top view of the guide vane carrier 1 is the arrangement of the inlet openings 17 and outlet openings 18 leading into and out of the guide vane carrier 1, which lead into the cooling channels 16 (not visible), clearly recognizable.
- the guide lugs 4 are arranged between the inlet openings 17 and outlet openings 18.
- the cylindrical section 3 with the lugs 4 'and coolant transfers indicated by arrows 23 to and from the (not shown) inlet segment 13 are shown.
- 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 area between the contact surfaces of the fastening screws 27, the outwardly open slots (according to FIGS. 9 and 10) being designed such that the expansion shafts of the expansion screws fill them whereby the threaded heads of the fastening screws 27 with nut supports 28 rest on the comb profiles 24.
- the outer contour of the comb profiles 24 runs approximately in a straight line.
- the nut supports 28 are provided under the nuts of the expansion screws 27, which have a cylindrical underside, which in turn is in a corresponding groove simultaneously 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 27 from the side. Since the cylindrical bearing surfaces permit rotary movements about their cylinder axes, this configuration becomes insensitive to an inclined position of the screws 27 at least in one plane and thus permits 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)
Claims (4)
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE8080200461T DE3071161D1 (en) | 1980-05-19 | 1980-05-19 | Cooled turbine stator |
AT80200461T ATE16035T1 (de) | 1980-05-19 | 1980-05-19 | Gekuehlter leitschaufeltraeger. |
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 EP0040267A1 (fr) | 1981-11-25 |
EP0040267B1 true 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) |
Families Citing this family (17)
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 |
US5626909A (en) | 1994-12-07 | 1997-05-06 | General Electric Company | Fabrication of brazable in air tool inserts |
US5685693A (en) * | 1995-03-31 | 1997-11-11 | General Electric Co. | Removable inner turbine shell with bucket tip clearance control |
DE19546722B4 (de) * | 1995-12-14 | 2005-03-31 | Alstom | Leitschaufelträger für eine Gasturbine |
RU2182976C2 (ru) * | 1996-06-21 | 2002-05-27 | Сименс Акциенгезелльшафт | Турбинный вал, а также способ охлаждения турбинного вала |
DE19643716A1 (de) | 1996-10-23 | 1998-04-30 | Asea Brown Boveri | Schaufelträger für einen Verdichter |
FR2761119B1 (fr) * | 1997-03-20 | 1999-04-30 | Snecma | Stator de compresseur de turbomachine |
EP0919700B1 (fr) * | 1997-06-19 | 2004-09-01 | 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 |
EP2159384A1 (fr) * | 2008-08-27 | 2010-03-03 | Siemens Aktiengesellschaft | Support statorique d'aubes directrices 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 |
FR3101105B1 (fr) * | 2019-09-23 | 2021-09-10 | Safran Aircraft Engines | Carter pour turbomachine et turbomachine équipée d’un tel carter |
Family Cites Families (17)
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 |
US2489683A (en) * | 1943-11-19 | 1949-11-29 | Edward A Stalker | Turbine |
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 |
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 |
CH425341A (de) * | 1965-07-23 | 1966-11-30 | Bbc Brown Boveri & Cie | Gasturbine mit Kühlung der Schaufelträger |
CH467930A (de) * | 1967-07-12 | 1969-01-31 | Escher Wyss Ag | Verfahren zum Betreiben einer Dampf- oder Gasturbine mit von Arbeitsmittel durchströmten Wärmeaustauschkanälen in Gehäuseteilen grösserer Materialstärke, sowie Einrichtung zur Durchführung dieses Verfahrens |
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 |
CH488098A (de) * | 1968-04-10 | 1970-03-31 | Licentia Gmbh | Einrichtung zur Kühlung der Flansche an den Gehäuseteilfugen von Sattdampf- oder Nassdampfturbinen |
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 |
-
1980
- 1980-05-19 EP EP80200461A patent/EP0040267B1/fr not_active Expired
- 1980-05-19 AT AT80200461T patent/ATE16035T1/de not_active IP Right Cessation
- 1980-05-19 DE DE8080200461T patent/DE3071161D1/de not_active Expired
-
1981
- 1981-04-28 JP JP6351181A patent/JPS5710707A/ja active Granted
- 1981-05-04 US US06/260,336 patent/US4386885A/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
JPS5710707A (en) | 1982-01-20 |
US4386885A (en) | 1983-06-07 |
ATE16035T1 (de) | 1985-10-15 |
DE3071161D1 (en) | 1985-11-14 |
EP0040267A1 (fr) | 1981-11-25 |
JPS648173B2 (fr) | 1989-02-13 |
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