EP1456508B1 - Heissgaspfad-baugruppe einer gasturbine - Google Patents
Heissgaspfad-baugruppe einer gasturbine Download PDFInfo
- Publication number
- EP1456508B1 EP1456508B1 EP02805240A EP02805240A EP1456508B1 EP 1456508 B1 EP1456508 B1 EP 1456508B1 EP 02805240 A EP02805240 A EP 02805240A EP 02805240 A EP02805240 A EP 02805240A EP 1456508 B1 EP1456508 B1 EP 1456508B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- gas
- subassembly
- cooling
- permeable
- impermeable
- 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 - Fee Related
Links
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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
- 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
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
-
- 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
- F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
-
- 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
- F01D25/12—Cooling
-
- 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
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/612—Foam
Definitions
- the present invention relates to a hot gas path assembly for a turbomachine, in particular for a gas turbine, according to the preamble of claim 1. It further relates to a turbomachine in which an assembly according to the invention is used.
- JP 61149506 shows a similar configuration in which the honeycomb seals are carried by a layer of porous metal adjacent to a supply chamber for cooling air. Also in this embodiment, the cooling air is brought through the honeycomb seals to the blade tips.
- a problem with a variety of configurations is that when it comes to one by rubbing Damage to the gas-permeable elements comes or even an area is completely torn out, the Coolant pressure collapses, and it becomes one Overheating and finally failure of the whole Seal arrangement comes.
- the coolant flows around this area of the sealing element. Whose Cooling is no longer guaranteed, and it comes to local overheating. Due to overheating, the burning out affected area. By the way resulting large hole now flows the cooling air out, and the previously unaffected areas become no longer cooled. As a result, the Bautiel fails as a whole, on the entire circumference.
- a hot gas path assembly of the above specify the type mentioned, which the disadvantages of Prior art avoids.
- a Hot gas path assembly be designed such that the Cooling air is used as efficiently as possible, and that in a damaged area of the Sealing element, the cooling of not immediately affected areas are essentially unimpaired remains. In other words, a potential possible damage to the location of the primary be limited to a damage-causing event.
- the core of the invention is therefore on the one hand, in a cooling air path to two cooling points in series too switch, such that the flowing cooling air successively to fulfill two cooling tasks is used.
- the Invention is with the same cooling air flow of the stator a gas turbine once in the area Leitschaufelsch, as well as in the area of a Cooled bucket row, and at the same time are the Bucket tips or the bucket cover with the same cooling air applied. This way will achieves the maximum permissible cooling air heating and the Cooling potential of the cooling air is maximally utilized.
- the partition wall is such stated that the cooling air flow paths of individual in the circumferential direction of the machine next to each other arranged segments downstream of a baffle cooling element hermetically separated.
- One Impact cooling element is comparatively with a variety provided small openings over which a Cooling air flow at high speed on the Cooling side of the component to be cooled is directed.
- baffle plates are used. by virtue of this function cause the baffle elements a comparatively high pressure drop, and are the essential throttle in the respective Coolant path, which also essentially the Metering of the flowing coolant causes. at a corresponding distribution of pressure drops, wherein the pressure loss coefficient of the impingement cooling element greater is, preferably at least a factor of 2, than the Pressure loss coefficient arranged downstream thereof Flow cross sections, the total flow is in first approximation only by the impingement cooling element certainly.
- each segment at least a single gas permeable Arranged element.
- the assembly according to the invention is very special then on, when the gas-permeable element a Part of a non-contact seal of a Turbomachine, in particular between a vane and the rotor and especially between one Blade and the stator is.
- the gas impermeable element in the direction of Hot gas flow upstream of the gas permeable Element arranged. It is advantageous if the gas impermeable element has another, redundant, Has coolant opening on the hot gas side the module opens.
- the coolant opening is as possible executed that there emerging coolant as possible parallel to the hot gas side surface of the gas-permeable element flows, such that there a cooling film is created.
- the Flow cross-sections of the gas-permeable element and the coolant openings in design terms so are measured that the pressure loss of the Coolant opening is greater than that of the gas-permeable element, such that preferably less than 50%, and in particular less than 30% of the total coolant through the coolant hole, and the rest as Transpiration coolant through the gas permeable Element is passed. If its pressure loss due to the effects described above, the coolant moves into the coolant opening, and the proportion of film cooling increases. As above set out, while the entire remains Coolant mass flow to a first approximation constant, if the pressure loss over the impingement cooling bores predominates.
- the inventive assembly is suitable as already indicated, very special for use in Turbomachinery, the gas-permeable elements a circumferential ring for non-contact sealing form with an opposite blade ring. preferably also form the gas-impermeable elements a circumferential ring; This ring is preferred in Direction of Heisssgas slideströmung the Turbomachine upstream of the ring of arranged gas permeable elements.
- the gas impermeable Elements of impact-cooled heat discharge segments in a Another preferred embodiment of the wear impact-cooled gas-impermeable elements Turbine blades, in particular vanes.
- the assembly according to the invention arranged in the stator of the turbomachine.
- the assembly is part a turbomachine is a preferred Embodiment that the dividers or Partition walls for subdividing the segments parallel to the chords of in the flow channel, and in particular on the gas impermeable elements, arranged blades run.
- the assembly consists in one embodiment a number of lateral, in particular in the circumferential direction, juxtaposed subassemblies, which so are constructed that each subassembly one gas impermeable element and a gas permeable Element comprises.
- an impingement cooling element spaced apart, and opposite of the gas permeable element a cover element.
- Such subassembly at least one Subdivision wall for fluid-separating subdivision and / or delineation of the annular gap in lateral direction, in particular in the circumferential direction.
- annular assembly in Circumferential direction in at least four from each other Independently with cooling medium acted upon segments be divided.
- the reliability of cooling is added Damage to individual sections of the increased gas permeable elements.
- honeycombs including porous, for example, produced by foaming Structures of metal or ceramic materials in Question, or felts or fabrics of metallic or ceramic fibers, in question.
- the present device are further means for independent of each other at least some of the segments provided with coolant.
- This can be realized by a device that the Supply of cooling medium to the individual segments via the respective supply channels independently controls. In this way, an inhomogeneous Temperature distribution during operation of the Turbomachine over the circumference of the flow channel be compensated by individual segments. With supplied accordingly adjusted amounts of cooling medium become. This is still suitable for the realization a gap width control.
- Figure 1 shows a section of a Flow channel of a turbomachine, for example a turbine of a gas turbine group.
- the flow channel is from right to left of a hot gas flow 12 flows through.
- a vane foot 16 with one Guide vane 10 is arranged in the stator 13 . Downstream of the vane 10 is a blade 11 with a shroud 7 and Shroud tips 7a arranged.
- the shroud tips minimize in conjunction with opposite arranged suitable stator 2, the leakage gap and thus the hot gas leakage flow 12a.
- the opposite element 2 is the normal case comparatively soft touch-tolerant element.
- the inventive, fixed in the stator, Assembly further includes an upstream of the gas permeable element 2 arranged gas-impermeable, impact-cooled element 8, here a Heat shield. Coolant, in particular cooling air or steam, via a feed 14 in the housing 13th introduced.
- the coolant 4 is initially high Speed through openings or nozzles of a Impact cooling element 17 out, and hits with high Impulse on the cooling side of the element 8, this being is cooled by impingement cooling.
- the coolant 4 continues to flow through after completion of the impingement cooling gas-permeable element 2 as transpiration coolant in the hot gas flow, wherein in the present Configuration continues the bucket cover 7 and the Seal tip 7a to be cooled. From this Coolant guide results in the best possible Utilization of the coolant 4. As can be seen, is between the gas-permeable element 2, the gas impermeable element 8, an upstream Wall 22, a downstream wall 23, the Impact cooling element 17, and a cover element 21 a in principle annular or ring segment-shaped space or gap 5, 9 is formed. According to the invention this in the circumferential direction of the turbomachine divided as below in particular in connection with Figure 3 is explained in more detail.
- FIG. 2 Another embodiment of the invention is in Figure 2 shown. Essential elements are explained In the light of the explanation of Figure 1 by itself.
- This embodiment serves the gas-impermeable Crash-cooled element 8 at the same time as a blade root 16 of the vane 10.
- Analogous to Figure 1 is between the gas-permeable element 2, the gas-impermeable Element 8, the impingement cooling element 17, a cover element 21, and an upstream wall 22 and a downstream wall 23, a space 9 is formed, which in the circumferential direction not recognizable here is divided. Coolant passes through the Impact cooling element 17 in the space 9 a. Under undisturbed nominal conditions, the coolant 4 flows at least predominantly by the gas permeable Element 2 off.
- the gas impermeable Element 8 another, redundant coolant port 18th on, via the coolant 4 flow out of the room 9 can.
- This coolant opening opens on the Heisgasseite the assembly that exiting there Coolant as a cooling film on the hot gas side of the gas-permeable element flows.
- the redundant Coolant opening is preferably dimensioned such that under undisturbed nominal conditions less than that Half, in particular less than 30%, of the Coolant mass flow 4 through the redundant Coolant openings 18 flow. If it does, though for example due to pollution or a Grazing event to a significant increase in the Flow resistance of the gas-permeable element.
- FIG. 3 shows a schematic view of a inventive assembly in one Cross-sectional view.
- Essentially radial and axially extending webs or partition walls 24 divide the space 9 in the circumferential direction into segments 26.
- Each segment 26 is also its own redundant Coolant opening 18 is arranged; at least theirs Mouth is slot-shaped, in case of need a the largest possible distribution of film coolant to achieve.
- This is the entire coolant path at least downstream of the impingement cooling elements 17 through the Partition walls 24 in completely from each other divided into independent segments.
- the Subassembly a partition wall 24, which en a peripheral side of the subassembly or on a other circumferential position can be arranged.
- the Subdivision wall is designed so that they, as in In connection with FIG. 3, a fluid separation is explained between the two peripheral sides manufactures.
- FIG. 5 shows a schematic Top view of the subassembly from the radial outside, with "split" walls 22, 23, 24. It can be seen that in this preferred embodiment the in the Figure 5 is not explicitly marked, but for the One skilled in the light of the foregoing recognizable, space 9 in the circumferential direction of one Dividing wall 14 divided in the circumferential direction that is parallel to the dot-dash line drawn chord of the blade 10 extends.
- the partition wall 24 is directly at one Peripheral side of the subassembly arranged; she could but without further ado another Be arranged circumferential position.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Sie betrifft weiterhin eine Strömungsmaschine, in welcher eine erfindungsgemässe Baugruppe verwendet wird.
Die JP 61149506 zeigt eine ähnliche Ausgestaltung, bei der die Wabendichtungen von einer Schicht aus porösem Metall getragen werden, die an eine Zufuhrkammer für Kühlluft angrenzt. Auch bei dieser Ausgestaltung wird die Kühlluft durch die Wabendichtungen hindurch an die Schaufelspitzen herangebracht.
- 1
- Trägerelement
- 2
- gasdurchlässiges Element
- 4
- Kühlmittel
- 5
- Raum, Spalt
- 7
- Schaufeldeckband
- 7a
- Dichtspitze
- 8
- gasundurchlässiges Element
- 9
- Kühlmittelkanal, Spalt
- 10
- Leitschaufel
- 11
- Laufschaufel
- 12
- Heissgasströmung
- 12a
- Leckageströmung
- 13
- Gehäusewandung, Stator
- 14
- Zuführung für Kühlmittel
- 16
- Schaufelfuss
- 17
- Prallkühlelement, Prallkühlblech, Prallkühleinsatz
- 18
- redundante Kühlmittelöffnung
- 21
- Deckelement
- 22
- stromaufwärtige Begrenzung, Wand
- 23
- stromabwärtige Begrenzung, Wand
- 24
- Unterteilungswand, Umfangs- oder laterale Unterteilungswand
- 26
- Segment
Claims (14)
- Heissgasspfad-Baugruppe für eine Strömungsmaschine, insbesondere für eine Gasturbine, welche Heissgaspfad-Baugruppe im Wesentlichen einen ringförmigen oder ringsegmentförmigen Querschnitt mit einer Umfangsrichtung aufweist, und welche Baugruppe eine Kühlseite und eine im Betrieb von Heissgas (12) überströmte Heissgasseite aufweist, welche Heissgaspfad-Baugruppe weiterhin umfasst: wenigstens ein für Transpirationskühlung ausgeführtes gasdurchlässiges Element (2) und wenigstens ein gasundurchlässiges Element (8), wobei das gasdurchlässige Element und das gasundurchlässige Element in Heissgas-Strömungsrichtung an unterschiedlichen Positionen angeordnet sind,
und wobei das gasundurchlässige Element prallgekühlt, mit einem auf der Kühlseite beabstandet von dem gasundurchlässigen Element angeordneten Prallkühlelement (17), ausgeführt ist, und wobei auf der Kühlseite der Baugruppe ein Kühlmittelpfad (9, 5) ausgebildet ist, der von dem Prallkühlelement (17) zu der Kühlseite des gasdurchlässigen Elementes (2) führt,
dadurch gekennzeichnet, dass die Baugruppe wenigstens eine Unterteilungswand (24) aufweist, welche den Kühlmittelpfad in Umfangsrichtung in fluidisch getrennte Segmente (26) unterteilt. - Baugruppe nach Anspruch 1, dadurch gekennzeichnet, dass, insbesondere in Umfangsrichtung, mehrere einzelne gasdurchlässige Elemente nebeneinander angeordnet sind.
- Baugruppe nach Anspruch 2, dadurch gekennzeichnet, dass in jedem Segment (26) wenigstens ein einzelnes gasdurchlässiges Element angeordnet ist.
- Baugruppe nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass das gasdurchlässige Element ein Dichtungselement einer Anordnung zur berührungslosen Dichtung ist.
- Baugruppe nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass auf dem gasundurchlässigen Element (8) ein Schaufelblatt (10) angeordnet ist.
- Baugruppe nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass das gasundurchlässige Element (8) in Heissgas-Strömungsrichtung (12) stromauf des gasdurchlässigen Elementes (2) angeordnet ist.
- Baugruppe nach Anspruch 5, dadurch gekennzeichnet, dass die Unterteilungswände (24) im Wesentlichen parallel zu den Profilsehnen der auf der Baugruppe angeordneten Schaufelblättern (10) verlaufen.
- Baugruppe nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass in dem gasundurchlässigen Element eine Kühlmittelöffnung angeordnet ist, welche stromauf des gasdurchlässigen Elementes auf der Heissgasseite mündet.
- Baugruppe nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass die Baugruppe aus einer Anzahl von in Umfangsrichtung nebeneinander angeordneten Unterbaugruppen besteht.
- Strömungsmaschine, insbesondere Gasturbine, umfassend wenigstens eine Baugruppe gemäss einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass die gasdurchlässigen Elemente (2) einen umlaufenden Ring zur berührungslosen Abdichtung mit einem gegenüberliegend angeordneten Schaufelkranz (11, 7, 7a) bilden.
- Strömungsmaschine nach Anspruch 10, dadurch gekennzeichnet, dass die gasundurchlässigen Elemente (8) einen umlaufenden Ring ausbilden, der in Strömungsrichtung einer Heissgasströmung (12) stromauf der gasdurchlässigen Elemente (2) angeordnet ist.
- Strömungsmaschine nach einem der Ansprüche 10 oder 11, dadurch gekennzeichnet, dass die gasundurchlässigen Elemente (8) prallgekühlte Wärmestausegmente sind.
- Strömungsmaschine nach einem der Ansprüche 10 bis 12, dadurch gekennzeichnet, dass die gasundurchlässigen Elemente (8) Schaufelblätter (10) tragen.
- Strömungsmaschine nach einem der Ansprüche 10 bis 13, dadurch gekennzeichnet, dass die Baugruppe im Stator (13) der Strömungsmaschine angeordnet ist.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH22792001 | 2001-12-13 | ||
CH227901 | 2001-12-13 | ||
PCT/CH2002/000686 WO2003054360A1 (de) | 2001-12-13 | 2002-12-12 | Heissgaspfad-baugruppe einer gasturbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1456508A1 EP1456508A1 (de) | 2004-09-15 |
EP1456508B1 true EP1456508B1 (de) | 2005-08-31 |
Family
ID=4568373
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP02805240A Expired - Fee Related EP1456508B1 (de) | 2001-12-13 | 2002-12-12 | Heissgaspfad-baugruppe einer gasturbine |
Country Status (6)
Country | Link |
---|---|
US (1) | US7104751B2 (de) |
EP (1) | EP1456508B1 (de) |
JP (1) | JP2005513330A (de) |
AU (1) | AU2002366846A1 (de) |
DE (1) | DE50204128D1 (de) |
WO (1) | WO2003054360A1 (de) |
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DE102014217832A1 (de) * | 2014-09-05 | 2016-03-10 | Rolls-Royce Deutschland Ltd & Co Kg | Kühlvorrichtung und Flugzeugtriebwerk mit Kühlvorrichtung |
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US6612806B1 (en) * | 1999-03-30 | 2003-09-02 | Siemens Aktiengesellschaft | Turbo-engine with an array of wall elements that can be cooled and method for cooling an array of wall elements |
EP1124039A1 (de) * | 2000-02-09 | 2001-08-16 | General Electric Company | Vorrichtung zur Prallkühlung des Deckbandes in einer Gasturbine |
US6340285B1 (en) * | 2000-06-08 | 2002-01-22 | General Electric Company | End rail cooling for combined high and low pressure turbine shroud |
-
2002
- 2002-12-12 EP EP02805240A patent/EP1456508B1/de not_active Expired - Fee Related
- 2002-12-12 AU AU2002366846A patent/AU2002366846A1/en not_active Abandoned
- 2002-12-12 WO PCT/CH2002/000686 patent/WO2003054360A1/de active IP Right Grant
- 2002-12-12 DE DE50204128T patent/DE50204128D1/de not_active Expired - Lifetime
- 2002-12-12 JP JP2003555048A patent/JP2005513330A/ja not_active Withdrawn
-
2004
- 2004-06-14 US US10/865,749 patent/US7104751B2/en not_active Expired - Fee Related
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102014217832A1 (de) * | 2014-09-05 | 2016-03-10 | Rolls-Royce Deutschland Ltd & Co Kg | Kühlvorrichtung und Flugzeugtriebwerk mit Kühlvorrichtung |
Also Published As
Publication number | Publication date |
---|---|
US20040258517A1 (en) | 2004-12-23 |
AU2002366846A1 (en) | 2003-07-09 |
DE50204128D1 (de) | 2005-10-06 |
JP2005513330A (ja) | 2005-05-12 |
EP1456508A1 (de) | 2004-09-15 |
WO2003054360A1 (de) | 2003-07-03 |
US7104751B2 (en) | 2006-09-12 |
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