EP1138881B1 - Turbinengehäuse für eine axial durchströmte Gasturbine - Google Patents
Turbinengehäuse für eine axial durchströmte Gasturbine Download PDFInfo
- Publication number
- EP1138881B1 EP1138881B1 EP01106613A EP01106613A EP1138881B1 EP 1138881 B1 EP1138881 B1 EP 1138881B1 EP 01106613 A EP01106613 A EP 01106613A EP 01106613 A EP01106613 A EP 01106613A EP 1138881 B1 EP1138881 B1 EP 1138881B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- outer shell
- turbine
- inner component
- gas space
- axial
- 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 - Lifetime
Links
- 239000000463 material Substances 0.000 claims description 14
- 238000007789 sealing Methods 0.000 claims description 12
- 239000007789 gas Substances 0.000 description 38
- 238000002485 combustion reaction Methods 0.000 description 7
- 230000000694 effects Effects 0.000 description 4
- 238000005266 casting Methods 0.000 description 3
- 238000010276 construction Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 239000003779 heat-resistant material Substances 0.000 description 2
- 230000000630 rising effect Effects 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 230000035882 stress Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000005304 joining Methods 0.000 description 1
- 239000012528 membrane Substances 0.000 description 1
- 230000009885 systemic effect Effects 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
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
- F01D25/26—Double casings; Measures against temperature strain in casings
-
- 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
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
Definitions
- the present invention relates to a turbine housing for an axially flowed gas turbine, the at least a hot gas space between a compressor stage and a turbine stage encloses and an outer shell as outer boundary as well as an interior component comprising the hot gas space via a gap separated from the outer shell.
- the object of the present invention is in it, a turbine housing for an axially flowed through
- the inexpensive to manufacture is and very high pressures and temperatures withstand. So is the turbine housing in the area of a Compressor pressure of over 30 bar at temperatures from 550 to 570 ° C can be operated easily.
- the task is with the turbine housing according to claim 1 solved.
- Advantageous embodiments of this Housing are the subject of the dependent claims.
- the invention Turbine housing, the at least one hot gas space between a compressor stage and a turbine stage encloses and an outer shell as outer boundary has one, separated from the outer shell provided inner component, which the hot gas space via a Interspace separated from the outer shell.
- the interior component is so over two axial interfaces connected to the outer shell that the gap is sealed against the hot gas space.
- the inner component is between the axial Clamped interfaces, so that the connection unit of the outer shell by in axial direction acting surface squeeze he follows.
- the turbine housing according to the invention is thus made an outer shell and an inner component assembled.
- the arrangement of the two components has the between the inner component and the outer shell formed gap a lower pressure and a lower temperature than that enclosed by the inner component Hot gas space. This is especially through allows the sealing of the gap from the hot gas space.
- About suitable feeds to this gap can be set in a predefinable pressure.
- the inner component hereinafter also as hot gas component designated, such that it both the hoop stresses due to the pressure difference between hot gas space and gap as well as the high withstand the temperature prevailing in the hot gas space.
- This hot gas component is therefore preferably made of a made of high quality material.
- the outer shell has only one sufficient have stiff construction on the one hand, the static Transfer forces of the gas turbine and on the other hand the pressure difference between the gap and the Ambient atmosphere to be able to withstand.
- the temperature, which acts on the outer shell is due to the Separation from the hot gas space via the inner component and significantly reduced the gap. This temperature load can by a suitable cooling air flow in between the inner member and the outer shell formed gap are additionally counteracted. This also reduces this in steam and gas turbines well-known phenomenon of the so-called "Katzbuckelns" the usually caused by a deformation of the stator becomes.
- the outer shell preferably has two inwardly directed circumferential Projections or webs as axial interfaces, on which the inner component touches down.
- the interior component This requires sufficient flexibility in the axial direction have over the entire operating cycle of the gas turbine at the axial interfaces to the outer housing enough surface pressure for the sealing effect to be achieved build.
- the sealing effect is preferably achieved by metallic sealing, with both the axial interfaces as well as the ones in contact coming surfaces of the inner component metallic sealing surfaces exhibit.
- the outer shell needs with the webs a sufficiently rigid construction have to due to the surface pressure for absorb metallic densities occurring axial forces.
- the materials for the outer shell and the Interior component chosen such that during operation a sufficient surface pressure between the interfaces the components is present for sealing.
- the thermal coefficient of linear expansion of the material for the inner component is preferably chosen lower as the one for the outer shell. Different thermal Strains due to acting on both components different temperatures can be compensated become.
- the materials will be in any case chosen so that the sealing effect between the inner component and the outer shell during operation not subsides.
- the turbine housing according to the invention allows Furthermore, that even under high pressure conditions of Compressor and large diameters of components smaller Separating flange fittings as well as simpler materials and geometries for the outer shell and the inner component can be chosen. This too leads to a reduction in the cost of providing a such turbine housing.
- FIG. 1 An example of a turbine housing for an axial perfused gas turbine is shown schematically in Figure 1.
- the figure shows the upper part of the symmetrically about a central axis 8 arranged housing structure.
- the central axis corresponds to the axis the gas turbine, along which the shaft with the turbine and compressor blades passes.
- the housing is made from the outer shell 1 and the inner component 2. Both enclose the hot gas space in the present case 5 ring-like.
- On the right side closes the (not shown) compressor stage 7, on the left Side of the expansion space 6 with the (not shown) Turbine stage.
- the combustion chamber wall 9 In the hot gas space 5 is the combustion chamber wall 9 (only schematically) indicated.
- Form the combustion chamber can be arbitrary. Here you can both annular combustion chambers and multi-stage combustion chambers, as known in the art, be provided.
- the hot gas space 5 contains from the compressor stages 7 incoming compressed air on high Temperature as well as the escaping from the combustion chamber hot gases.
- the hot gas space 5 is enclosed by the inner component 2. Between the inner component 2 and the outer shell 1, an annular space 3 is formed, which over the axial interfaces 4 sealed from the hot gas space 5 is.
- the interfaces 4 are metallic sealing surfaces formed on the end surfaces of the inner component Press 2, so that a surface pressure for metallic densities is effected.
- the interior component 2 This is during assembly with a defined mounting gap clamped between the two interfaces 4. In the transient driving range, during takeoff and parking, takes on an additional element (e.g., a built-in membrane seal) the sealing function. In normal operation, the outer shell 1 and inner component 2 braced together.
- the interfaces themselves are in this case as radially encircling elevations or webs executed, the sealing surfaces vertically to the central axis 8 run.
- Both outer shell 1 as well as inner component 2 have in this area outwardly arched shape. This shape is the Clamping of the inner component 2 between the two axial interfaces 4 supported.
- the seal between the hot gas space 5 and the Annulus 3 allows significantly different pressure conditions in the annulus than those present in the hot gas space.
- the Inner component 2 thus only needs the pressure difference between Hot gas space and annulus carry while the outer shell 1 only the pressure difference between Annulus 3 and the environment 10, that is the atmospheric pressure, as well as the static forces of the gas turbine must withstand.
- the separation of the outer shell 1 from Hot gas space 5 via the inner component 2 and the annulus 3 further lowers the temperature load on the outer shell 1, so that these are made of normal heat-resistant Material can be manufactured.
- the outer shell 1, for example Stg41T be made while the higher temperature loads exposed interior component 2, for example made of the material Stg10T.
- Figure 2 shows the same embodiment again in a perspective sectional view.
- This view is the curved shape of the outer shell. 1 and the inner member 2 with the intermediate one Annular space 3 very easy to recognize.
- the two axial interfaces 4 through from the outer shell 1 inwardly directed circumferential webs are formed seen. These interfaces 4 are preferably made integral with the outer shell.
- the outer shell 1 of such a turbine housing can be made very easily with a casting technique become.
- the hot gas space 5 from the annular space 3 separating Inner component 2 then only has to be between the two Interfaces 4 are clamped.
- Suitable material differences between the material the inner component 2 and the material of the outer shell 1 allow almost temperature independent Surface pressure of the inner component 2 on the axial Interfaces 4.
- the feeds for the supply of a medium for example a cooling medium like air, can not be seen in the annulus 3.
- About these feeds can be a predefinable pressure maintained in the annulus.
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)
- Gasket Seals (AREA)
Description
- Figur 1
- schematisch einen Schnitt durch ein beispielhaftes Turbinengehäuse; und
- Figur 2
- das Turbinengehäuse aus Figur 1 in perspektivischer Schnittansicht.
- 1
- Außenschale
- 2
- Innenbauteil
- 3
- Ringraum
- 4
- Axiale Schnittstelle
- 5
- Heißgasraum
- 6
- Expansionsraum (Turbinenstufe)
- 7
- Verdichterstufe
- 8
- Mittelachse
- 9
- Brennkammerwandung
- 10
- Umgebung
Claims (6)
- Turbinengehäuse für eine axial durchströmte Gasturbine, das zumindest einen Heißgasraum (5) zwischen einer Verdichterstufe (7) und einer Turbinenstufe (6) umschließt und eine Außenschale (1) als äußere Begrenzung sowie ein Innenbauteil (2) aufweist, das den Heißgasraum über einen Zwischenraum (3) von der Außenschale (1) abtrennt,
wobei das Innenbauteil (2) über zwei axiale Schnittstellen (4) derart mit der Außenschale (1) verbunden ist, daß der Zwischenraum (3) gegen den Heißgasraum (5) abgedichtet ist,
dadurch gekennzeichnet, daß das Innenbauteil (2) zwischen den axialen Schnittstellen (4) eingespannt ist, so daß die Verbindung mit der Außenschale (1) durch in axialer Richtung wirkende Flächenpressung erfolgt. - Turbinengehäuse nach Anspruch 1,
dadurch gekennzeichnet, daß die Außenschale (1) und das Innenbauteil (2) aus derart unterschiedlichen Werkstoffen gebildet sind, daß sich beim Betrieb der Gasturbine ausreichend Flächenpressung an den axialen Schnittstellen (4) einstellt, um den Zwischenraum (3) gegen den Heißgasraum (5) abzudichten. - Turbinengehäuse nach einem der Ansprüche 1 oder 2,
dadurch gekennzeichnet, daß die axialen Schnittstellen (4) als metallische Dichtflächen ausgebildet sind. - Turbinengehäuse nach einem der Ansprüche 1 bis 3,
dadurch gekennzeichnet, daß Außenschale (1) und Innenbauteil (2) den Heißgasraum (5) ringförmig umschließen. - Turbinengehäuse nach einem der Ansprüche 1 bis 4,
dadurch gekennzeichnet, daß das Innenbauteil (2) eine nach außen gewölbte Form aufweist. - Turbinengehäuse nach einem der Ansprüche 1 bis 5,
dadurch gekennzeichnet, daß die Außenschale (1) eine oder mehrere Öffnungen für die Zufuhr eines Mediums zum Zwischenraum (3) aufweist.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10016082A DE10016082A1 (de) | 2000-03-31 | 2000-03-31 | Turbinengehäuse für eine axial durchströmte Gasturbine |
DE10016082 | 2000-03-31 |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1138881A2 EP1138881A2 (de) | 2001-10-04 |
EP1138881A3 EP1138881A3 (de) | 2003-10-08 |
EP1138881B1 true EP1138881B1 (de) | 2005-08-03 |
Family
ID=7637141
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP01106613A Expired - Lifetime EP1138881B1 (de) | 2000-03-31 | 2001-03-16 | Turbinengehäuse für eine axial durchströmte Gasturbine |
Country Status (4)
Country | Link |
---|---|
US (1) | US6484511B2 (de) |
EP (1) | EP1138881B1 (de) |
CN (1) | CN1320764A (de) |
DE (2) | DE10016082A1 (de) |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
SE0300261D0 (sv) * | 2003-01-31 | 2003-01-31 | Electrolux Home Prod Corp | Refrigerator with drawer |
US7909569B2 (en) * | 2005-06-09 | 2011-03-22 | Pratt & Whitney Canada Corp. | Turbine support case and method of manufacturing |
US7784261B2 (en) * | 2006-05-25 | 2010-08-31 | Siemens Energy, Inc. | Combined cycle power plant |
US8393855B2 (en) * | 2007-06-29 | 2013-03-12 | General Electric Company | Flange with axially curved impingement surface for gas turbine engine clearance control |
US8197186B2 (en) | 2007-06-29 | 2012-06-12 | General Electric Company | Flange with axially extending holes for gas turbine engine clearance control |
CN109098780B (zh) * | 2018-05-24 | 2024-05-14 | 中车大连机车研究所有限公司 | 一种涡轮增压器燃气废气进排气壳体 |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2417835A (en) * | 1936-09-25 | 1947-03-25 | Harry H Moore | Combustion device |
US2575070A (en) * | 1948-04-06 | 1951-11-13 | William A Reed | Jacketed combustion pot with fuel and air nozzle head |
US2599654A (en) * | 1949-04-04 | 1952-06-10 | Curtiss Wright Corp | Stator blade construction |
US2702454A (en) * | 1951-06-07 | 1955-02-22 | United Aircraft Corp | Transition piece providing a connection between the combustion chambers and the turbine nozzle in gas turbine power plants |
US3088281A (en) * | 1956-04-03 | 1963-05-07 | Bristol Siddeley Engines Ltd | Combustion chambers for use with swirling combustion supporting medium |
US3772881A (en) * | 1970-06-04 | 1973-11-20 | Texaco Ag | Apparatus for controllable in-situ combustion |
US3842595A (en) * | 1972-12-26 | 1974-10-22 | Gen Electric | Modular gas turbine engine |
GB2168755B (en) * | 1984-12-08 | 1988-05-05 | Rolls Royce | Improvements in or relating to gas turbine engines |
US5657625A (en) | 1994-06-17 | 1997-08-19 | Mitsubishi Jidosha Kogyo Kabushiki Kaisha | Apparatus and method for internal combustion engine control |
JP3564286B2 (ja) * | 1997-12-08 | 2004-09-08 | 三菱重工業株式会社 | ガスタービン静翼の段間シールアクティブクリアランス制御システム |
DE19821889B4 (de) * | 1998-05-15 | 2008-03-27 | Alstom | Verfahren und Vorrichtung zur Durchführung von Reparatur- und/oder Wartungsarbeiten im Innengehäuse einer mehrschaligen Turbomaschine |
-
2000
- 2000-03-31 DE DE10016082A patent/DE10016082A1/de not_active Withdrawn
-
2001
- 2001-03-16 EP EP01106613A patent/EP1138881B1/de not_active Expired - Lifetime
- 2001-03-16 DE DE50106934T patent/DE50106934D1/de not_active Expired - Fee Related
- 2001-03-28 CN CN01109509A patent/CN1320764A/zh active Pending
- 2001-03-30 US US09/821,090 patent/US6484511B2/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
EP1138881A2 (de) | 2001-10-04 |
US20010025479A1 (en) | 2001-10-04 |
CN1320764A (zh) | 2001-11-07 |
US6484511B2 (en) | 2002-11-26 |
DE10016082A1 (de) | 2001-10-04 |
DE50106934D1 (de) | 2005-09-08 |
EP1138881A3 (de) | 2003-10-08 |
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