EP0424253B1 - Turbokompressorgehäuse mit Spielkontrollvorrichtung für den inneren Durchmesser - Google Patents

Turbokompressorgehäuse mit Spielkontrollvorrichtung für den inneren Durchmesser Download PDF

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Publication number
EP0424253B1
EP0424253B1 EP90402910A EP90402910A EP0424253B1 EP 0424253 B1 EP0424253 B1 EP 0424253B1 EP 90402910 A EP90402910 A EP 90402910A EP 90402910 A EP90402910 A EP 90402910A EP 0424253 B1 EP0424253 B1 EP 0424253B1
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EP
European Patent Office
Prior art keywords
compressor
casing
arms
turbine engine
engine according
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
Application number
EP90402910A
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English (en)
French (fr)
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EP0424253A1 (de
Inventor
Gilles Lucien Eugène Delrieu
Carmen Miraucourt
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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Publication of EP0424253A1 publication Critical patent/EP0424253A1/de
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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
    • F01D11/14—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

Definitions

  • the present invention relates to a turbomachine compressor casing provided with a device for controlling its internal diameter in order to ensure a minimum objective radial clearance between the ends of the moving blades of the compressor rotor and the corresponding surfaces of the stator or fixed part of compressor comprising said casing.
  • FR-A-2 535 795 or FR-A-2 534 982 where we also note the presence of fixing means connecting the inner envelope to the outer envelope.
  • FR-A-2534982 describes the closest state of the art according to the preamble of claim 1.
  • FR-A-2 577 282 combines the connecting rods between internal and external envelopes and ventilation means of the outer envelope.
  • One of the aims of the invention while avoiding the drawbacks of known prior solutions and facilitating implementation, is to allow a reduction in the consumption of ventilation air.
  • said hollow arms are cooled by impact with air supplied by perforated tubes arranged inside the arms and a collector collects the air going up to the radially external part of the arms.
  • a casing 1 of a turbomachine compressor comprises, on the one hand, a radially outer casing 2, comprising at each end of the radial flanges, respectively 3 and 4, oriented towards the outside and assembled by any known means such as bolts symbolized in 5 and 6 with flanges 7 and 8 of two housings respectively adjacent and , on the other hand, an internal casing 9, radially spaced from the previous one and which supports, according to a construction method known per se of axial compressors, a certain number of circular rows of fixed blades forming stator stages 10, 11, 12 three in number in the example shown in Figure 1 and between which are interposed stages of movable blades 13, 14, 15 of the compressor rotor.
  • Said internal casing 9 further relates to its internal diameter, in line with the ends of the moving blades of the circular bands 16, 17, 18 of abradable material.
  • the external envelope 2 is composed of two parts 2a and 2b, as shown diagrammatically in FIG. 2, joined together for example by means of bolts symbolized in 19, at the level of external longitudinal flanges 20.
  • the outer 2 and inner 9 envelopes are connected by a plurality of hollow arms 21, regularly distributed circumferentially, as in the example shown in FIG. 2 where the hollow arms 21 are 18 in number per row and arranged in two rows longitudinally spaced apart, as shown in FIG.
  • Each hollow arm 21 is fixed by its diametrically external end relative to the compressor on the external casing 2 by means of two bolts 22 each cooperating with a captive nut 23.
  • the radially internal end relative to the compressor of each hollow arm 21 carries an eyelet 24 cooperating with an axis 25 mounted on a yoke 26 secured to the casing pe internal 9.
  • a tube 27 with multiple perforations 28 Inside each hollow arm 21 is disposed a tube 27 with multiple perforations 28.
  • a sheet 29 closes the end of the space formed between the envelopes 2 and 9, thus forming an enclosure 30 and thus ensures sealing on the upstream side of said enclosure 30 in which said hollow arms 21 are placed.
  • a gap provided between the internal envelope 9 and the corresponding rim 31 of a neighboring distributor 32 provides an opening 33 supplying hot air taken from the fluid stream of the compressor said enclosure 30.
  • the inner casing 9 is also composed of two parts 9a and 9b, as shown diagrammatically in Figures 2 and 2a. These two parts 9a and 9b cooperate at the level of external longitudinal flanges 34. A clearance is provided on each face 34a opposite the two flanges 34 so as to form a housing 35 in which a seal 36 is placed in order to ensure sealing. between the flanges 34 without creating a fixed connection but allowing, on the contrary, the expansions / contractions of the internal envelope 9.
  • the tubes 27 of the hollow casing arms 21 are supplied with cooling air by conduits 37 in a manner known per se and which has not been shown in detail in the drawings.
  • the air sampling in the example shown in FIG. 1, is carried out from the low pressure compressor of the turbomachine, symbolized at 38.
  • a valve device 39 is interposed on the cooling air supply circuit between the sampling point at 38 and the tubes 27 of the hollow arms 21.
  • the device 39 is actuated from a control signal 40 prepared in a manner known per se as a function of the operating conditions of the turbomachine and according to a pre-established control program.
  • FIGS. 1 and 2 for the production of a turbomachine compressor casing are used for controlling the radial clearances between the rotor and the compressor stator in the above manner.
  • the outer 2 and inner 9 casings of the housing are made of materials whose coefficient of thermal expansion is chosen so as to obtain identical expansion in operation.
  • FIG. 3 gives an example of the evolution of the games in operation according to the conditions of use of the turbomachine.
  • the curve R thus shows the radial displacements of a point located on the compressor rotor, in particular at the radially external end of a movable blade, in the case of an operating cycle comprising an acceleration phase from '' a point A at the zero of the timescale on the abscissa to a point B, from which a deceleration phase begins.
  • Curve S shows the corresponding evolution of the displacements in the radial direction of a point of the stator, in particular the corresponding point located on the internal face of the internal casing 9 of the compressor casing, in line with the end of the moving dawn.
  • the rotor retracts more quickly than the casing due to the lowering of the effects due to mechanical expansions by centrifugal force and the lower thermal inertia of the blades. Then, in a second step, the effects of mechanical origin stabilize and the disc has a thermal inertia greater than that of the casing, it is therefore the latter which has the fastest retraction. If to hold account of the search for better performance of the turbomachine and in particular to improve efficiency and reduce specific consumption, the lowest possible radial clearance is provided between rotor and stator under stabilized operating conditions of the turbomachine at cruising speed, at point C of the deceleration in figure 3, a contact occurs between rotor and stator.
  • the ventilation circuit is open and the cooling air, impact cooling the hollow arms 21, through the perforations 28 of the tubes 27.
  • the retraction of the internal casing 9 of the compressor housing is thus delayed, avoiding contact between the rotor and the stator.
  • This operating phase can be very short compared to the entire cycle, for example of a duration of the order of 100 seconds, which greatly limits the air consumption notably required by other known control solutions. thermal ventilation games.
  • the impact cooling of the hollow arms 21 is supplemented by cooling by circulation of the air rising along the inside of said arms 21 towards the radially external part from which by passages 41 the air is recovered in a collector 42 disposed outside the casing, this air which can then in known manner be used for various easements, in particular on aircraft for cabin pressurization for example.
  • the ventilation circuit of the hollow arms 21 can be opened at will. in different phases of operation of the turbomachine, acceleration, cruising speed or re-acceleration for example, the advantage of the invention being to limit air consumption during periods when the need to maintain a minimum radial clearance between rotor and stator imposes act on the expansion / contraction of the compressor housing.
  • FIG 4 shows an alternative embodiment of the compressor housing according to the invention similar to that which has been shown in Figures 1 and 2.
  • the same or similar elements and in particular, the inner casing 9 in two parts the outer casing 102 has been brought closer to said inner casing 9, so as to reduce the diametrical size.
  • the construction of the hollow arms 121 has been slightly modified.
  • Their connection to the internal casing 9 by eyelet 24, axis 25 and yoke 26 remains identical as well as the arrangement of the inner tubes 27 and their connection to a ventilation circuit.
  • the connection of the hollow arms 121 to the external envelope 102 is radially offset towards the outside by means of bosses 43 integral with said external envelope 102.
  • the operating mode in this case is identical to that which has was previously described with reference to Figures 1 and 2.
  • This variant also has the advantage of having a faster response time.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (9)

  1. Turbomaschinen-Verdichtergehäuse mit einem aus zwei durch verschraubte Flansche (20) miteinander verbundenen Teilen (2a, 2b) bestehenden radial äußeren Mantel (2) und einem aus zwei Teilen (9a, 9b) bestehenden radial inneren Mantel (9), der mehrere Reihen von feststehenden, den Verdichterstator bildenden Schaufeln (10, 11, 12) und auf seiner Innenseite an der Stelle der Enden der beweglichen Schaufeln (13, 14, 15) des Verdichterrotors verschleißbare Bänder ( 16, 17, 18) trägt, wobei der Zwischenraum zwischen dem inneren und dem äußeren Mantel eine Kammer (30) bildet, die auf der stromaufwärtigen Seite von Dichtungsmitteln (29) verschlossen ist und durch eine mittels einer auf der stromabwärtigen Seite des inneren Mantels (9) angebrachten Öffnung (33) bewerkstelligte Entnahme im Fluidkanal des Verdichters mit heißer Luft gespeist wird, und wobei der innere Mantel (9) und der äußere Mantel (2) durch mehrere Verbindungsarme (21; 121) miteinander verbunden sind,
       dadurch gekennzeichnet,
       daß diese Verbindungsarme (21; 121) hohl sind und von Kühlluft durchströmt werden können, die über einen Belüftungskreis (27, 37, 41, 42) herangeführt und abgeführt wird.
  2. Turbomaschinen-Verdichtergehäuse nach Anspruch 1, bei dem die hohlen Verbindungsarme (21; 121) in ihrem Innern perforierte Rohre (27) enthalten, die Luft zur Aufprallkühlung heranführen, die anschließend in dem radial äußeren Teil der Arme an einen Sammler (42) abgegeben wird.
  3. Turbomaschinen-Verdichtergehäuse nach Anspruch 2, bei dem die hohlen Arme (21; 121) mit Kühlluft gespeist werden, die aus einem Niederdruckverdichter (38) abgezogen wird, und bei dem das Gehäuse (1) einen Hochdruckverdichter umschließt.
  4. Turbomaschinen-Verdichtergehäuse nach einem der Ansprüche 1 bis 3, bei dem die Verbindungsarme (21) mit ihrem radial äußeren Ende mit dem äußeren Mantel (2) und mit ihrem radial inneren Ende mit einer Achse (25) verschraubt sind, die an einem mit dem inneren Mantel (9) fest verbundenen Bügel (26) montiert ist.
  5. Turbomaschinen-Verdichtergehäuse nach einem der Ansprüche 1 bis 3, bei dem die Verbindungsarme (121) mit ihrem radial inneren Ende jeweils mit einer Achse (25) fest verbunden sind, die an einem mit dem inneren Mantel (9) fest verbundenen Bügel (26) montiert ist, und bei dem der äußere Mantel (102) in Höhe des radial inneren Teils der Arme (121) angeordnet ist, wobei das radial äußere Ende der Arme (121) an mit dem äußeren Mantel (102) fest verbundenen Vorsprüngen (43) angeschraubt ist.
  6. Turbomaschinen-Verdichtergehäuse nach einem der Ansprüche 1 bis 5, bei dem die beiden Teile (9a, 9b) des inneren Mantels (9) im Bereich von radialen Flanschen (34) zusammenwirken, in dem eine Aufnahme (35) für eine Dichtung (36) vorgesehen ist, die Dilationen/Kontraktionen des inneren Mantels (9) in radialer Richtung zuläßt.
  7. Turbomaschinen-Verdichtergehäuse nach einem der Ansprüche 1 bis 6, bei dem der innere Mantel (9) und der äußere Mantel (2; 102) aus Materialien bestehen, die einen solchen Wärmeausdehnungskoeffizienten haben, daß ihre Ausdehnungen im Betrieb identisch sind.
  8. Turbomaschinen-Verdichtergehäuse nach einem der Ansprüche 1 bis 7, bei dem der Belüftungskreis für die hohlen Arme (21; 121) des Gehäuses eine Anordnung von Ventilen (39) umfaßt, die in einer dem Verzögerungsbeginn entsprechenden Betriebsphase während einer zwischen einer und zwei Minuten liegenden reduzierten Zeitspanne die Speisung mit Kühlluft erlaubt.
  9. Turbomaschinen-Verdichtergehäuse nach einem der Ansprüche 1 bis 7, bei dem der Belüftungskreis für die hohlen Arme (21; 121) des Gehäuses eine Anordnung von Ventilen (39) umfaßt, die das Öffnen der Luftzufuhr zu den hohlen Arme des Gehäuses in jedem beliebigen Zeitpunkt in den unterschiedlichen Betriebsphasen der Turbomaschine ermöglicht.
EP90402910A 1989-10-18 1990-10-17 Turbokompressorgehäuse mit Spielkontrollvorrichtung für den inneren Durchmesser Expired - Lifetime EP0424253B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8913585A FR2653171B1 (fr) 1989-10-18 1989-10-18 Carter de compresseur de turbomachine muni d'un dispositif de pilotage de son diametre interne.
FR8913585 1989-10-18

Publications (2)

Publication Number Publication Date
EP0424253A1 EP0424253A1 (de) 1991-04-24
EP0424253B1 true EP0424253B1 (de) 1993-03-31

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP90402910A Expired - Lifetime EP0424253B1 (de) 1989-10-18 1990-10-17 Turbokompressorgehäuse mit Spielkontrollvorrichtung für den inneren Durchmesser

Country Status (4)

Country Link
US (1) US5154578A (de)
EP (1) EP0424253B1 (de)
DE (1) DE69001233T2 (de)
FR (1) FR2653171B1 (de)

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US5219268A (en) * 1992-03-06 1993-06-15 General Electric Company Gas turbine engine case thermal control flange
FR2708669B1 (fr) * 1993-08-05 1995-09-08 Snecma Système de ventilation des disques et du stator de turbine d'un turboréacteur.
US5685693A (en) * 1995-03-31 1997-11-11 General Electric Co. Removable inner turbine shell with bucket tip clearance control
US5779436A (en) * 1996-08-07 1998-07-14 Solar Turbines Incorporated Turbine blade clearance control system
US5791872A (en) * 1997-04-22 1998-08-11 Rolls-Royce Inc. Blade tip clearence control apparatus
DE19824766C2 (de) 1998-06-03 2000-05-11 Siemens Ag Gasturbine sowie Verfahren zur Kühlung einer Turbinenstufe
GB2388407B (en) * 2002-05-10 2005-10-26 Rolls Royce Plc Gas turbine blade tip clearance control structure
EP1426563A1 (de) 2002-12-03 2004-06-09 BorgWarner Inc. Turbolader mit keramischer oder metallischer Hitzeisolierung zwischen Turbinen- und Lagergehäuse
US6925814B2 (en) * 2003-04-30 2005-08-09 Pratt & Whitney Canada Corp. Hybrid turbine tip clearance control system
US20050109016A1 (en) * 2003-11-21 2005-05-26 Richard Ullyott Turbine tip clearance control system
EP1566531A1 (de) * 2004-02-19 2005-08-24 Siemens Aktiengesellschaft Gasturbine mit einem gegen Auskühlen geschützten Verdichtergehäuse und Verfahren zum Betrieb einer Gasturbine
US8240979B2 (en) * 2007-10-24 2012-08-14 United Technologies Corp. Gas turbine engine systems involving integrated fluid conduits
US8177494B2 (en) * 2009-03-15 2012-05-15 United Technologies Corporation Buried casing treatment strip for a gas turbine engine
US8342798B2 (en) * 2009-07-28 2013-01-01 General Electric Company System and method for clearance control in a rotary machine
US20110103939A1 (en) * 2009-10-30 2011-05-05 General Electric Company Turbine rotor blade tip and shroud clearance control
FR3034465B1 (fr) * 2015-04-03 2017-05-05 Snecma Turbomoteur comportant deux flux de ventilation distincts
US20170350597A1 (en) * 2016-06-07 2017-12-07 General Electric Company Heat transfer device, turbomachine casing and related storage medium
US10422237B2 (en) * 2017-04-11 2019-09-24 United Technologies Corporation Flow diverter case attachment for gas turbine engine
US10815814B2 (en) 2017-05-08 2020-10-27 Raytheon Technologies Corporation Re-use and modulated cooling from tip clearance control system for gas turbine engine

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FR2577282B1 (fr) * 1985-02-13 1987-04-17 Snecma Carter de turbomachine associe a un dispositif pour ajuster le jeu entre rotor et stator
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Also Published As

Publication number Publication date
EP0424253A1 (de) 1991-04-24
FR2653171A1 (fr) 1991-04-19
DE69001233D1 (de) 1993-05-06
FR2653171B1 (fr) 1991-12-27
US5154578A (en) 1992-10-13
DE69001233T2 (de) 1993-09-23

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