EP1512842A2 - Gasturbine mit Laufspaltkontrolle - Google Patents
Gasturbine mit Laufspaltkontrolle Download PDFInfo
- Publication number
- EP1512842A2 EP1512842A2 EP04018924A EP04018924A EP1512842A2 EP 1512842 A2 EP1512842 A2 EP 1512842A2 EP 04018924 A EP04018924 A EP 04018924A EP 04018924 A EP04018924 A EP 04018924A EP 1512842 A2 EP1512842 A2 EP 1512842A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- control ring
- segments
- gas turbine
- turbine according
- adjustable
- 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
Links
- 239000000463 material Substances 0.000 claims description 4
- 238000010276 construction Methods 0.000 description 4
- 230000002349 favourable effect Effects 0.000 description 3
- 239000000725 suspension Substances 0.000 description 3
- 230000006978 adaptation Effects 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 229910045601 alloy Inorganic materials 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 230000001360 synchronised 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
- 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
- F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
- F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
Definitions
- the invention relates to a gas turbine with several Shroud segments, which serve as sealing blades of a Turbine wheel enclose, with at least one front or a rear attachment of the shroud segments to the radial outer region of the vane segments, which on their inner area each stored on a control ring are.
- control ring serves the purpose of thermal Extend the control ring to use the vane segments according to the thermal conditions in theirs Adjust outer circumference. This causes a reduction or increasing the overall diameter of the through the shroud segments formed ring. This results in an adjustment the gap between the tips of the blades and the interior of the shroud segments. Otherwise, one would thermal contraction or expansion of the blades too an enlargement of the gap or to a contact with the Lead shroud segments.
- the prior art is therefore based on the basic idea, a to achieve optimal passive running gap control. This will, as described, achieved by the fact that the fastening means the shroud segments have a thermal performance, which with the radial movement of the blade tips of the Blades is synchronized. Instationary operating states Ideally, they can not be detrimental to the running gap in stationary operation.
- the invention is based on the object, a gas turbine with to create an optimized passive running gap control, which with a simple structure and cost-effective production and assembly has an optimized performance.
- the guide blade segments are mounted radially adjustable on the control ring.
- the construction according to the invention has a number of significant Advantages.
- Annular gap seal (running gap) compared to the basic design in Their dimensions can be optimized as an exact adaptation to the thermal performance is possible. In order to can be axisymmetric and eccentric position deviations be compensated without component change.
- the vane segments also in the circumferential direction are adjustably mounted on the control ring. So it is possible to make appropriate settings in the circumferential direction, before a final assembly of the vane segments and the shroud segments.
- adjustable storage By inventively provided adjustable storage the possibility is created during the assembly an exact Make setting and according to the assignment to optimize the components.
- the guide vane segments by means of a screw under Frictional engagement are fixed to the control ring. That's the way it is, for example possible a sleeve with a setting game or to provide a segment with a Einstellspiel.
- the setting also by an excenter device, for example a fitting sleeve with eccentric, done.
- control ring a secondary air seal is formed and the Control ring is designed so that its thermal performance the width of the annular gap of the secondary air seal controlled.
- the inside of the vane ring space arranged control ring is thereby designed to be thermal performance in addition to controlling the Running gap also for controlling at least one annular gap seal the rotor cooling air system (secondary air system) is used.
- the rotor cooling air system secondary air system
- at least one connected to the control ring secondary air seal as a brush seal or multi-level labyrinth be executed.
- Fig. 3 shows the shroud segment 1 which the Leitschaufelsegment the HDT 7 and the vane segment of the NDT 12 assigned. On the design of the housing and the herein located cooling air channels is omitted at this point.
- the reference numeral 11 relates to a secondary air seal, the may be formed in the form of a brush seal.
- Reference numeral 15 represents a housing of the HDT.
- FIG. 3 The general structure of the arrangement shown in Fig. 3 corresponds in broad terms the prior art, the invention Variants show in particular the enlarged FIG. 1 and 2.
- Fig. 1 is in addition to those already occupied by reference numerals and described components, the attachment of the Guide vane segments 7 shown on the control ring 9.
- the control ring 9 is provided with an insulation 16 which is the thermal behavior of the thermal behavior of the disc 5 approaches.
- the attachment takes place by means of a sleeve 17 and a Screw 18, wherein additionally a load compensation element 19th is provided.
- the sleeve has a setting game, the fixation via the screw by means of the screw 18th with friction.
- the vane segment 7 both in the radial and in the circumferential direction in a certain To adjust the dimensions.
- the Load compensation element 19 becomes the inner blade suspension 14 relieved and can thereby be dimensioned smaller become. This has a favorable effect on weight and costs of the entire construction.
- Each blade is thus by means of a screw 18 to the Control ring 9 screwed.
- the sleeve 17 is located in the lower Bar of the vane (vane segment 7).
- the sleeve can, seen from the center of the sleeve, forces only in the radial direction transferred to the vane.
- the vane can thus, as described, in the axial direction and the circumference tip over the middle of the tube.
- the bore diameter of the sleeve has a game on screw diameter, then that Adjustability of the vanes to the control ring allows.
- At least one brush seal formed as an integral part of the control ring is.
- the selection of the respective materials (alloys) is made in such a way that an adaptation to the thermal Behavior and the joining technical concerns of the control ring takes place and the connection of the brush seal to the control ring is possible without releasable fasteners.
- control ring and its positive axial connection to the vane segments are designed in accordance with the invention an outer seal is formed on the control ring.
- an outer seal is formed on the control ring. In connection with the inner seal on the control ring is ensured a pressure gradient across the control ring for load compensation at the location of the inner blade hanger leads.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- Fig. 1
- eine vergrößerte Teilansicht des vorderen Steuerrings unter Verwendung der Erfindung,
- Fig. 2
- eine vergrößerte Teilansicht des hinteren Steuerrings unter Verwendung der Erfindung, und
- Fig. 3
- eine Teil-Gesamtansicht der erfindungsgemäßen passiven Laufspaltkontrolle.
- 1
- Deckbandsegment
- 2
- Mutter
- 3
- Laufschaufel
- 4
- Mutter
- 5
- Turbinenrad
- 6
- Innere Lastaufnahme für 7
- 7
- Leitschaufelsegment der HDT
- 8
- Äußere Dichtung vorderer Steuerring
- 9
- Vorderer Steuerring
- 10
- Hinterer Steuerring
- 11
- Sekundärluftdichtung
- 12
- Leitschaufelsegment der NDT
- 13
- Innere Dichtung vorderer Steuerring
- 14
- Innere Laufschaufelaufhängung
- 15
- Gehäuse
- 16
- Isolation
- 17
- Hülse
- 18
- Schraube
- 19
- Lastkompensationselement
- 20
- Dichtung
- 21
- Schraube
- 22
- Segment
Claims (10)
- Gasturbine mit mehreren Deckbandsegmenten (1), welche als Dichtung Laufschaufeln (3) eines Turbinenrades (5) umschließen, wobei zumindest eine vordere und eine hintere Befestigung der Deckbandsegmente (1) an dem radial äußeren Bereich von Leitschaufelsegmenten (7,12) erfolgt, welche an ihrem radial inneren Bereich jeweils an einem Steuerring (9,10) gelagert sind, dadurch gekennzeichnet, dass die Leitschaufelsegmente (7,12) radial einstellbar an dem Steuerring (9,10) gelagert sind.
- Gasturbine nach Anspruch 1, dadurch gekennzeichnet, dass die Leitschaufelsegmente (7,12) in Umfangsrichtung einstellbar an dem Steuerring gelagert sind.
- Gasturbine nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die Leitschaufelsegmente (7,12) mittels einer Verschraubung unter Kraftschluss an dem Steuerring (9,10) fixiert sind.
- Gasturbine nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die Leitschaufelsegmente (7,12) mittels eines Einstellspiels relativ zu dem Steuerring (9,10) verstellbar sind.
- Gasturbine nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die Leitschaufelsegmente (7,12) mittels einer Excentervorrichtung relativ zu dem Steuerring (9,10) verstellbar sind.
- Gasturbine nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die Leitschaufelsegmente (7,12) mittels einstellbarer Segmente relativ zu dem Steuerring (9,10) verstellbar sind.
- Gasturbine nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass an dem Steuerring (9,10) zumindest eine Sekundärluftdichtung (11) ausgebildet ist, und dass der Steuerring (9,10) so ausgestaltet ist, dass sein thermisches Betriebsverhalten die Breite des Ringspalts der Sekundärluftdichtung (11) steuert.
- Gasturbine nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass die Materialien der Elemente zumindest eines Steuerringes so ausgewählt sind, dass deren thermischer Ausdehnungskoeffizient mindestens 15% kleiner ist als der der benachbarten Rotorscheibe (5).
- Gasturbine nach einem der Ansprüche 1 bis 8, dadurch gekennzeichnet, dass sich an den Leitschaufelsegmenten (7) eine Lastkompensationseinrichtung befindet.
- Gasturbine nach einem der Ansprüche 1 bis 9, dadurch gekennzeichnet, dass es sich um eine mehrstufige Turbine handelt, wobei der vordere Bereich der ersten Deckbandsegmente in den Leitschaufelsegmenten gelagert ist, die sich vor dem ersten Turbinenrad befinden und der hintere Bereich der letzten Deckbandsegmente in den Leitschaufelsegmenten gelagert ist, die sich hinter dem letzten Turbinenrad befinden.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10340825A DE10340825A1 (de) | 2003-09-04 | 2003-09-04 | Gasturbine mit Laufspaltkontrolle |
DE10340825 | 2003-09-04 |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1512842A2 true EP1512842A2 (de) | 2005-03-09 |
EP1512842A3 EP1512842A3 (de) | 2006-04-05 |
EP1512842B1 EP1512842B1 (de) | 2009-07-22 |
Family
ID=34129646
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04018924A Expired - Fee Related EP1512842B1 (de) | 2003-09-04 | 2004-08-10 | Gasturbine mit Laufspaltkontrolle |
Country Status (3)
Country | Link |
---|---|
US (1) | US7306428B2 (de) |
EP (1) | EP1512842B1 (de) |
DE (2) | DE10340825A1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1712744A1 (de) * | 2005-04-14 | 2006-10-18 | Rolls-Royce Deutschland Ltd & Co KG | Anordnung zur inneren passiven Laufspalteinstellung bei einer Hochdruckturbine |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7160078B2 (en) * | 2004-09-23 | 2007-01-09 | General Electric Company | Mechanical solution for rail retention of turbine nozzles |
US9200530B2 (en) | 2012-07-20 | 2015-12-01 | United Technologies Corporation | Radial position control of case supported structure |
US9500095B2 (en) | 2013-03-13 | 2016-11-22 | Pratt & Whitney Canada Corp. | Turbine shroud segment sealing |
US9394801B2 (en) | 2013-10-07 | 2016-07-19 | General Electric Company | Adjustable turbine seal and method of assembling same |
US9206700B2 (en) * | 2013-10-25 | 2015-12-08 | Siemens Aktiengesellschaft | Outer vane support ring including a strong back plate in a compressor section of a gas turbine engine |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2061396A (en) * | 1979-10-24 | 1981-05-13 | Rolls Royce | Turbine blade tip clearance control |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4688378A (en) * | 1983-12-12 | 1987-08-25 | United Technologies Corporation | One piece band seal |
US5141394A (en) * | 1990-10-10 | 1992-08-25 | Westinghouse Electric Corp. | Apparatus and method for supporting a vane segment in a gas turbine |
US5149250A (en) * | 1991-02-28 | 1992-09-22 | General Electric Company | Gas turbine vane assembly seal and support system |
US5224822A (en) * | 1991-05-13 | 1993-07-06 | General Electric Company | Integral turbine nozzle support and discourager seal |
US5372476A (en) * | 1993-06-18 | 1994-12-13 | General Electric Company | Turbine nozzle support assembly |
US5921749A (en) * | 1996-10-22 | 1999-07-13 | Siemens Westinghouse Power Corporation | Vane segment support and alignment device |
US6095750A (en) * | 1998-12-21 | 2000-08-01 | General Electric Company | Turbine nozzle assembly |
-
2003
- 2003-09-04 DE DE10340825A patent/DE10340825A1/de not_active Withdrawn
-
2004
- 2004-08-10 EP EP04018924A patent/EP1512842B1/de not_active Expired - Fee Related
- 2004-08-10 DE DE502004009777T patent/DE502004009777D1/de active Active
- 2004-09-03 US US10/933,257 patent/US7306428B2/en not_active Expired - Fee Related
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2061396A (en) * | 1979-10-24 | 1981-05-13 | Rolls Royce | Turbine blade tip clearance control |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1712744A1 (de) * | 2005-04-14 | 2006-10-18 | Rolls-Royce Deutschland Ltd & Co KG | Anordnung zur inneren passiven Laufspalteinstellung bei einer Hochdruckturbine |
US7588414B2 (en) | 2005-04-14 | 2009-09-15 | Rolls-Royce Deutschland Ltd & Co Kg | Arrangement for internal passive turbine blade tip clearance control in a high pressure turbine |
Also Published As
Publication number | Publication date |
---|---|
US20050089400A1 (en) | 2005-04-28 |
DE10340825A1 (de) | 2005-03-31 |
DE502004009777D1 (de) | 2009-09-03 |
EP1512842A3 (de) | 2006-04-05 |
EP1512842B1 (de) | 2009-07-22 |
US7306428B2 (en) | 2007-12-11 |
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