EP1006264B1 - Kühlbarer Mantel für eine Turbomaschine - Google Patents
Kühlbarer Mantel für eine Turbomaschine Download PDFInfo
- Publication number
- EP1006264B1 EP1006264B1 EP99811095A EP99811095A EP1006264B1 EP 1006264 B1 EP1006264 B1 EP 1006264B1 EP 99811095 A EP99811095 A EP 99811095A EP 99811095 A EP99811095 A EP 99811095A EP 1006264 B1 EP1006264 B1 EP 1006264B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- segments
- guide
- casing
- casing according
- guide segments
- 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
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
- 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
-
- 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
- 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
- F01D25/246—Fastening of diaphragms or stator-rings
-
- 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 coolable jacket of a gas turbine or the like according to the preamble of claim 1.
- the mantle is formed by several arcuate shell segments formed, which in the circumferential direction adjoining a shroud form, which surrounds a rotor of a high-pressure turbine stage.
- an annular jacket cooling chamber provided, extending in the radial direction between the shroud segments and arcuate guide segments extends.
- the leading segments are off Sheet sections formed, which provided with a plurality of through holes are.
- an air guide chamber is present, extending in the radial direction between the guide segments and a housing-side carrier or carrier segment extends.
- the carrier further comprises an air supply passage, the opens into the air duct chamber.
- Cooling air is fed into the air supply duct to cool the jacket. From there it passes through the through-holes, using high-speed air jets form, which is essentially perpendicular to the Impact rear side of the shell segments. After the impact, they are redirected and there is a cross flow in the jacket cooling chamber.
- the invention seeks to avoid the disadvantages described. She is the one
- the object of the invention is to specify a coolable jacket of the type mentioned in the introduction, the constructively simple constructed without serious loss of cooling efficiency is, whereby both the manufacturing and the repair and Reduce maintenance costs.
- the mechanical stresses reduced in the described transient processes and thus an increased life can be achieved.
- this is achieved by providing a coolable jacket according to the preamble of claim 1, the guide segments loose and with radial Game are stored.
- This type of storage are relative movements between the carrier or carrier segment and the sheath segments possible.
- the radial clearance is such that a largely unimpeded relative movement Also for the worst transient operating state is possible. This occurs during the run-up phase, in which the guide segments acted upon with cooling air which has a comparatively high temperature, by contrast the carrier is still comparatively cold.
- a particularly simple structural design can then be realized if the guide segments are guided loosely between the carrier and spacers, the spacers projecting in the radial direction at the back of the Sheath segments are attached.
- the impinging on the guide segments cooling air flow pushes it against the spacers, creating a fixed distance maintained between the leading segments and the back of the shell segments becomes.
- the jacket cooling chamber is fixed in the radial direction, the radial extent of which corresponds to the height of the spacers.
- the comparatively high pressure, under which the cooling air is supplied, ensures that the Guide segments during the period of exposure to cooling air safely against the spacers are kept pressed.
- a particularly secure storage of the guide segments can then be achieved if they are provided with at least two radial webs, which with low axial play engage in corresponding guide grooves of the carrier.
- the low clearance allows on the one hand the radial displacement movement of the guide segments, On the other hand minimizes the leakage due to lateral flow around the guide segments even with a comparatively high overpressure of the cooling air supply.
- the configuration of the guide segments with a U-shaped Cross-sectional profile that is particularly easy to manufacture.
- a non-cutting Forming process can each be formed laterally thighs, as in Circumferentially passing webs the exact guidance of the respective guide segment to ensure.
- the guide segments are arranged overlapping in the circumferential direction. This creates a continuous, uninterrupted separation surface in the circumferential direction between the jacket cooling chamber and the air supply duct, so that Leakage losses at the crossing points of two adjacent arranged Lead segments are further minimized.
- an increased number of through holes may be provided to be in this area also the formation of cooling air jets in to provide sufficient quantities. This takes the effect into account carried that by the loose storage of the individual Leitsegmente the relative allocation can vary in the circumferential direction, associated with the risk that im Overlap area too few through holes of two overlapping guide segments be brought to cover.
- each shell segment and carrier In the contact area between each shell segment and carrier are in the circumferential direction extending flange portions provided so that shell segment and Carrier by means of retaining clips, which each adjoining flange sections embrace, are detachably connected to each other.
- the retaining clips On the one hand press the shell segments and carrier firmly together, so that Leakage losses due to exiting cooling air between the two components largely is prevented.
- the retaining clips allow a simple Loosen and restore the connection so that not only the assembly of the Mantels, but especially the repair by replacing individual Elements is greatly simplified.
- flange sections ensure a virtually complete seal in the contact area between shell segment and carrier. This can be the Keep cooling demand at a low level.
- Fig. 1 It is a section of the first high-pressure turbine stage a gas turbine, consisting of an impeller 110 and a stator 120 shown.
- the impeller 110 is in the radial direction of a shroud surrounded, consisting of several, lined up in the circumferential direction shell segments 10 is constructed.
- Each shell segment 10 is associated with a carrier segment 20, which in not shown in detail on a housing 100 is fixed.
- the carrier segment 20 is in a substantially radial direction from an air supply passage 26 passes through the cooling air from a non-illustrated Cooling air supply is supplied.
- a cooling air for example, a partial air flow used from one of the upstream compressor stages.
- the air supply duct 26 opens into a circumferentially continuous recess 24, which is part of an air guide chamber 25.
- the air guiding chamber 25 becomes radial bounded on the inside by a guide segment 30.
- the guide segment 30 has a U-shaped basic shape with two webs 32, which designed in corresponding Guide grooves 22 of the carrier segment 20 engage.
- the guide segment 30 is supported on two formed as ribs Spacers 12 from extending in the circumferential direction and in radial Direction protruding at the back of the shell segment 10 are attached.
- a jacket cooling chamber 15th arises in the radial direction between the shell segment 10 and the Guide segment 30, a jacket cooling chamber 15th
- the guide segments 30 are of a plurality provided by passage openings 34, which has a fluid connection between represent the air guide chamber 25 and the jacket cooling chamber 15 and the Training of cooling air jets serve.
- the carrier segment 20 and the shell segment 10 have flange portions 28 or 18, which are covered by retaining clips 80 and thus the Carrier segment 20 and the shell segment 10 connect together.
- the retaining clips 80 have an approximately U-shaped cross-sectional profile with two axial webs 89, in the corresponding axial grooves 29, 19 of the support segment 20th or the shell segment 10 engage. This creates an axial aligned transition from the carrier segment 20 to the shell segment 10th
- Sealing elements 90 are in corner regions between the retaining clips 80 on the one hand and the flange portions 28 of the support segment 20 and the Flange portions 18 of the shroud segment 10 on the other hand used to a largely pressure-tight closure between the air-conducting areas, in particular the jacket cooling chamber 15 and the air guide chamber 25 and to ensure the environment.
- the guide segments 30 are for forming in the circumferential direction continuous air-conducting channels arranged overlapping. As can be seen from FIG. 2, two abutting guide segments 30 are arranged in each case an overlap area 38 results. For this purpose, the leading segments Each formed at one end so that they in the adjacent Guide segment 30 can be inserted. The outer contour gives way to this slightly inward back, so that in the transition region 38 a kind Leadership results.
- the peculiarity of the present design consists in the fact that the guide segments 30 are loosely supported with some radial play and thus a relative movement between the carrier segment 20 and the guide segment 30 allows becomes.
- This relative movement allows in particular the tension-free compensation different thermal expansion during transient operating conditions, such as during startup of the gas turbine, in which the components have different temperatures.
- the carrier segment 20 still cold (for example ambient temperature)
- the guide segment 30 already by cooling air higher temperature from one of the compressor stages is heated strongly.
- cooling air acts on the guide segment 30 and pushes this radially inwardly directed against the ribs 12 of the Shroud segment 10.
- Continuous cooling air supply creates a pressure difference maintained between the air guide chamber 25 and the jacket cooling chamber 15, so that the guide segment 30 is securely fixed during operation.
- the maintenance of the pressure difference is necessary to the aimed to realize impact cooling by cooling air jets, which by the Through openings 34 are generated.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
- Fig. 1
- Kühlbarer Mantel im Axialschnitt (Teilansicht);
- Fig. 2
- Überlappungsbereich zweier aneinandergrenzender Leitsegmente in perspektivischer Ansicht.
- 10
- Mantelsegment
- 12
- Abstandshalter, Rippe
- 15
- Mantelkühlkammer
- 18
- Flanschabschnitt
- 19
- Axialnut
- 20
- Trägersegment
- 22
- Führungsnut
- 24
- Vertiefung
- 25
- Luftführungskammer
- 26
- Luftzuführungskanal
- 28
- Flanschabschnitt
- 29
- Axialnut
- 30
- Leitsegment
- 32
- Steg
- 34
- Durchgangsöffnung
- 38
- Überlappungsbereich
- 80
- Halteklammer
- 89
- Axialsteg
- 90
- Dichtungselement
- 100
- Gehäuse
- 110
- Laufrad
- 120
- Leitrad
Claims (10)
- Kühlbarer Mantel einer Gasturbine mitmehreren bogenförmigen Mantelsegmenten (10), die in Umfangsrichtung aneinandergrenzend zu einem im Wesentlichen geschlossenen, ein Laufrad (110), insbesondere einer Hochdruckturbine, umgebenden Mantelring angeordnet sind,wenigstens einer ringförmigen Mantelkühlkammer (15), die in radialer Richtung zwischen den Mantelsegmenten (10) und bogenförmigen, mit einer Vielzahl von Durchgangsöffnungen (34) versehenen Leitsegmenten (30) gebildet ist,wenigstens einer Luftführungskammer (25), die in radialer Richtung zwischen den Leitsegmenten (30) und wenigstens einem Trägersegment (20) gebildet ist, sowiewenigstens einem, an dem Trägersegment (20) angebrachten Luftzuführungskanal (26), der in die Luftführungskammen (25) mündet,
- Mantel nach Anspruch 1,
dadurch gekennzeichnet, dass die Leitsegmente (30) lose zwischen dem Trägersegment (20) und Abstandshaltem (12) geführt sind, welche in radialer Richtung abstehend an der Rückseite der Mantelsegmente (10) angebracht sind. - Mantel nach Anspruch 2,
gekennzeichnet durch Abstandshalter (12) in Form von Stegen, Rippen, Pins oder Auflageerhebungen. - Mantel nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass die Leitsegmente (30) radiale Stege (32) aufweisen, die mit geringem axialem Spiel in Führungsnuten (22) des Trägersegments (20) geführt sind. - Mantel nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass die Leitsegmente (30) ein U-förmiges Querschnittsprofil aufweisen. - Mantel nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass die Leitsegmente (30) in Umfangsrichtung überlappend angeordnet sind. - Mantel nach Anspruch 6,
dadurch gekennzeichnet, dass die Leitsegmente (30) im Überlappungsbereich (38) eine erhöhte Anzahl von Durchgangsöffnungen (34) aufweisen. - Mantel nach Anspruch 6,
dadurch gekennzeichnet, dass die Leitsegmente (30) im Überlappungsbereich (38) Durchgangsöffnungen mit vergrößerter Fläche aufweisen. - Mantel nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass die Mantelsegmente (10) und die Trägersegmente (20) in Axialrichtung weisende Flanschabschnitte (18; 28) aufweisen und mittels die Flanschabschnitte (18; 28) umgreifender Halteklammern (80) miteinander lösbar verbunden sind. - Mantel nach Anspruch 9,
gekennzeichnet durch Dichtungselemente (90) zwischen den Halteklammern (80) einerseits und den Flanschabschnitten (18; 28) andererseits.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19855130 | 1998-11-30 | ||
DE19855130A DE19855130A1 (de) | 1998-11-30 | 1998-11-30 | Kühlbarer Mantel einer Gasturbine oder dergleichen |
US09/450,728 US6322320B1 (en) | 1998-11-30 | 1999-11-30 | Coolable casing of a gas turbine or the like |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1006264A2 EP1006264A2 (de) | 2000-06-07 |
EP1006264A3 EP1006264A3 (de) | 2003-10-22 |
EP1006264B1 true EP1006264B1 (de) | 2005-01-05 |
Family
ID=26050451
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP99811095A Expired - Lifetime EP1006264B1 (de) | 1998-11-30 | 1999-11-26 | Kühlbarer Mantel für eine Turbomaschine |
Country Status (4)
Country | Link |
---|---|
US (1) | US6322320B1 (de) |
EP (1) | EP1006264B1 (de) |
JP (1) | JP4489882B2 (de) |
DE (1) | DE19855130A1 (de) |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1329594A1 (de) * | 2002-01-17 | 2003-07-23 | Siemens Aktiengesellschaft | Regelung des Blattspitzenspalts einer Gasturbine |
US8613589B2 (en) * | 2008-03-31 | 2013-12-24 | Pebble Bed Modular Reactor (Pty) Limited | Thermal insulation structure for structural member, and scroll structure |
US8079804B2 (en) * | 2008-09-18 | 2011-12-20 | Siemens Energy, Inc. | Cooling structure for outer surface of a gas turbine case |
US8092161B2 (en) | 2008-09-24 | 2012-01-10 | Siemens Energy, Inc. | Thermal shield at casing joint |
US8128344B2 (en) * | 2008-11-05 | 2012-03-06 | General Electric Company | Methods and apparatus involving shroud cooling |
US9255524B2 (en) * | 2012-12-20 | 2016-02-09 | United Technologies Corporation | Variable outer air seal fluid control |
US9494081B2 (en) | 2013-05-09 | 2016-11-15 | Siemens Aktiengesellschaft | Turbine engine shutdown temperature control system with an elongated ejector |
DE102013216392A1 (de) * | 2013-08-19 | 2015-02-19 | MTU Aero Engines AG | Vorrichtung und Verfahren zur Regelung der Temperatur eines Bauteils einer Strömungsmaschine |
US10975721B2 (en) | 2016-01-12 | 2021-04-13 | Pratt & Whitney Canada Corp. | Cooled containment case using internal plenum |
FR3082872B1 (fr) * | 2018-06-25 | 2021-06-04 | Safran Aircraft Engines | Dispositif de refroidissement d'un carter de turbomachine |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4013376A (en) * | 1975-06-02 | 1977-03-22 | United Technologies Corporation | Coolable blade tip shroud |
GB2047354B (en) * | 1979-04-26 | 1983-03-30 | Rolls Royce | Gas turbine engines |
US4337016A (en) * | 1979-12-13 | 1982-06-29 | United Technologies Corporation | Dual wall seal means |
US4551064A (en) * | 1982-03-05 | 1985-11-05 | Rolls-Royce Limited | Turbine shroud and turbine shroud assembly |
FR2548733B1 (fr) * | 1983-07-07 | 1987-07-10 | Snecma | Dispositif d'etancheite d'aubages mobiles de turbomachine |
US4642024A (en) * | 1984-12-05 | 1987-02-10 | United Technologies Corporation | Coolable stator assembly for a rotary machine |
US4921401A (en) * | 1989-02-23 | 1990-05-01 | United Technologies Corporation | Casting for a rotary machine |
US5116199A (en) * | 1990-12-20 | 1992-05-26 | General Electric Company | Blade tip clearance control apparatus using shroud segment annular support ring thermal expansion |
US5169287A (en) | 1991-05-20 | 1992-12-08 | General Electric Company | Shroud cooling assembly for gas turbine engine |
US5167488A (en) * | 1991-07-03 | 1992-12-01 | General Electric Company | Clearance control assembly having a thermally-controlled one-piece cylindrical housing for radially positioning shroud segments |
DE19619438B4 (de) * | 1996-05-14 | 2005-04-21 | Alstom | Wärmestausegment für eine Turbomaschine |
-
1998
- 1998-11-30 DE DE19855130A patent/DE19855130A1/de not_active Ceased
-
1999
- 1999-11-26 EP EP99811095A patent/EP1006264B1/de not_active Expired - Lifetime
- 1999-11-30 JP JP34084399A patent/JP4489882B2/ja not_active Expired - Fee Related
- 1999-11-30 US US09/450,728 patent/US6322320B1/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
JP4489882B2 (ja) | 2010-06-23 |
EP1006264A3 (de) | 2003-10-22 |
JP2000192802A (ja) | 2000-07-11 |
US6322320B1 (en) | 2001-11-27 |
EP1006264A2 (de) | 2000-06-07 |
DE19855130A1 (de) | 2000-05-31 |
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