EP2078822A1 - Gasturbinenmotor mit Klappenventil für die Verbindung von zwei Behältern - Google Patents

Gasturbinenmotor mit Klappenventil für die Verbindung von zwei Behältern Download PDF

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Publication number
EP2078822A1
EP2078822A1 EP09150354A EP09150354A EP2078822A1 EP 2078822 A1 EP2078822 A1 EP 2078822A1 EP 09150354 A EP09150354 A EP 09150354A EP 09150354 A EP09150354 A EP 09150354A EP 2078822 A1 EP2078822 A1 EP 2078822A1
Authority
EP
European Patent Office
Prior art keywords
valve
slider
turbine
chamber
tubular element
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
Application number
EP09150354A
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English (en)
French (fr)
Other versions
EP2078822B1 (de
Inventor
Aurélien René-Pierre Massot
Jean-Pierre Pabion
Sébastien Jean Laurent Prestel
Jean-Luc Soupizon
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
SNECMA SAS
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Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP2078822A1 publication Critical patent/EP2078822A1/de
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Publication of EP2078822B1 publication Critical patent/EP2078822B1/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
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations

Definitions

  • the present invention relates to the field of gas turbine engines and aims a means controlling the flow of air between two enclosures inside the engine, the relative pressure between the two speakers varying according to the operating regime.
  • a gas turbine engine comprises at least three parts: an air compressor, a combustion chamber and a turbine, the compressor supplying the combustion chamber which produces hot gases driving the turbine.
  • the turbine is connected to the compressor by a shaft by which it drives the latter.
  • the engine may comprise several bodies each with a rotor formed of a compressor, a turbine and a shaft connecting them mechanically.
  • Engines in the aeronautical field are generally double or triple bodies. They therefore comprise at least one rotary body operating with a low pressure motor fluid, BP, and a rotary body operating with a high pressure motor fluid, HP, the two bodies being mechanically independent of each other and rotating at different speeds.
  • a blowing fluid distribution chamber is provided between the outer wall of the transition channel and a turbine casing member.
  • the enclosure communicates through a fluid supply port with a sampling zone upstream of the transition channel. This sampling is preferably performed at the compressor so that the injected air forms a thermal protection film of the wall.
  • the annular gas stream is delimited externally by a stator ring.
  • the clearance between the top of the blades of the HP turbine and the inner face of this ring is maintained, during all phases of operation of the engine, as low as possible because the efficiency of the turbine depends on it.
  • the HP stator and rotor assembly being subjected in operation to different axial and radial relative displacements, it follows a variation of the game that should be controlled.
  • air drawn upstream from the engine, at the level of the compressor is used to ventilate the support of the stator ring and to control its expansion as a function of the speed.
  • the air circulating in the ventilation chamber is then discharged into the vein. This is in itself known.
  • the piloting involves a non-continuous ventilation air circulation. This flow of air is reduced and interrupted, especially when the speed is stabilized.
  • the engine comprises both such a means for controlling the expansion of the turbine stator ring with a flow of ventilation air, flowing in a ventilation chamber, and a blowing air distribution chamber immediately downstream, arranged around the wall of the transition channel
  • this ventilation air as at least a portion of the blowing air of the outer wall of the vein in the transition channel.
  • the differential pressure between said ventilation chamber and the blowing air distribution chamber is likely to change.
  • the circulation ventilation air is interrupted or reduced, the pressure in the ventilation chamber becomes lower than that of the distribution chamber. If a communication between the two speakers existed, a parasitic reflux of gas from the distribution chamber, disrupting the control of the clearance between the stator ring and the top of the turbine blades, would be created.
  • a double-body gas turbine engine comprising a stator ring of HP turbine and an outer wall of the transition channel between the HP and LP stages, a first chamber for controlling the stator ring, and a second chamber for the distribution of blowing air of the outer wall of the transition channel , characterized in that the two enclosures are placed in communication by an orifice whose opening is controlled by a valve arranged to be open when the pressure P1 in the first chamber is greater than the pressure P2 in the second chamber, and closed when P1 ⁇ P2.
  • the invention is advantageous with a motor whose two enclosures are separated by a partition pierced with said orifice.
  • the valve comprises a tubular element engaged in the orifice, with a flared part, a shut-off slide movable in the tubular element between a closed position bearing against the flared part and a position of unobstructed opening of the flared portion.
  • the tubular element may have been reported in the orifice or alternatively form a single piece with the partition.
  • the valve comprises a perforated cover, attached to the tubular element, against which the slide bears in the open position.
  • the valve comprises a closure slider with a leakage orifice providing a reduced flow of gas between the distribution chamber and the ventilation chamber, in the closed position.
  • This solution is advantageous because it makes it possible to avoid an excessive gap in pressure between the enclosures.
  • the valve comprises a tubular element comprising a part with a reduced diameter, a part of more large diameter, the two parts being connected by the flared portion, the slide having a guide surface portion cooperating with the larger diameter portion for guiding the slider inside the tubular member.
  • the valve comprises a tubular element comprising a part with a reduced diameter, a part of larger diameter, the two parts being connected by the flared part, the slide comprising a portion of the guiding surface cooperating with the diameter part. reduced for guiding the slider inside the tubular element.
  • FIG. 1 schematically, an example of a turbomachine in the form of a turbofan and double-body turbojet engine is shown schematically.
  • a fan 2 at the front, supplies the engine with air.
  • the compressed air by the fan is divided into two concentric flows.
  • the secondary flow is evacuated directly into the atmosphere without further energy input and provides an essential part of the driving thrust.
  • the primary flow is guided through several stages of compression to the combustion chamber 5 where it is mixed with the fuel and burned.
  • the compression is carried out successively by a booster compressor fixed in rotation with the fan rotor and forming part of the LP rotor, then by an HP compressor.
  • the hot gases of the combustion chamber feed the various turbine stages, the HP turbine 6 and the LP turbine 8.
  • the turbine rotors BP and HP are secured respectively to the LP rotors and Compressor HP, they drive the blower and the moving wheels of the compressor.
  • the gases are then vented to the atmosphere.
  • the HP turbine is a single stage while, for the LP turbine, the trigger is split between several stages mounted on the same rotor.
  • a transition channel is provided between the two sections HP and BP, more precisely between the rotor of the HP turbine and the inlet valve of the LP turbine. Due to the relaxation of the gases, the volume increases and the average diameter of the vein too. However, this increase remains compatible with undisturbed flow conditions.
  • the profile of the aerodynamic channel is optimized. Among these optimizations is the increase of the low pressure turbine inlet slope in the transition channel which allows a rapid increase in the average radius of the low pressure turbine. In addition, this increase in low pressure distributor inlet section generated by a greater diffusion in the channel, gives rise to an increase in performance on the first stage with better acceleration in the distributor.
  • blowing One solution is to inject a significant flow of gas at the outlet of the high pressure turbine at the wall. This air injection is commonly called blowing.
  • the figure 2 represents a portion of the casing of a gas turbine engine at the HP turbine and the input of the transition channel downstream thereof.
  • the rotor of the HP turbine which shows the blade 14, is rotatable within an annular space defined externally by a stator ring 15 forming a sealing means. Downstream of the turbine, the engine gas stream is delimited externally by the wall 20. This wall is formed of platforms in ring sectors extending axially between the turbine stator ring 15 and the distributor of the first stage of the LP turbine not visible in the figure.
  • the stator ring 15 is itself formed of sectors mounted in an annular piece 16, intermediate.
  • the sectors of the ring 15 are retained here by tongue and groove connections on the upstream side and by clamps downstream.
  • the intermediate piece 16 is mounted in an inner casing member 17 housed inside the outer casing 11.
  • the inner casing 17 comprises two radial ribs 17a and 17b, arranged annularly in two transverse planes passing through the rotor of the HP turbine.
  • An annular sheet 12 covers the ribs 17a and 17b and is supported by a radial flange 12r against the inner face of the outer casing 11.
  • a ventilation chamber 19 is thus formed between the sheet 12 and the inner casing 17.
  • the ribs 17a and 17b are pierced with axial orifices 17a1 and 17b1 allowing the flow of gas between the zone upstream of the ribs and the zone downstream of the ribs. Ventilation is provided by a gas flow F from an appropriate passage provided upstream of the ventilation enclosure 19.
  • a blast air distribution chamber 21 Downstream of a radial flange 17c of the inner casing 17, a blast air distribution chamber 21 is formed by a metal sheet which is shaped so as to have a substantially radial upstream partition 21a, a downstream partition 21b, also oriented globally. radially, a radially inner partition 21c and a radially outer partition 21d. A sealing gasket 22 lamella is placed between the radial flange 17c of the inner casing 17 and the partition 21a.
  • the enclosure 21 communicates with the enclosure 19 through an orifice 21a1 equipped with a valve 30.
  • the enclosure 21 communicates with the gas stream through an opening 21c1, made in the radially inner partition 21c, a tube 23 and openings 20a along the wall 20 of the transition channel.
  • the valve 30 is shown in more detail on the figure 3 . It comprises a tubular portion 31, a slider 33 and a perforated lid 35.
  • the tubular portion 31 is formed of a first cylindrical portion 31a of diameter d1, a second cylindrical portion 31c of larger diameter d2, d2> d1, and a flared portion 31b, connecting the two cylinders 31a and 31c.
  • the slide is housed in the large diameter portion 31c with a shaped face to cover the flared portion.
  • the slider 33 is pierced with orifices 33a arranged annularly and a central orifice 33b. Great The diameter of the slide corresponds to the internal diameter of the cylindrical portion 31c.
  • the cover 35 mounted on this part forms an axial stop for the slide.
  • the slide can take an open position, resting against the cover, in which case the openings 33a are released.
  • the slider 33 can take a closed or closed position when it bears against the flared portion 31b. In this position the orifices 33a are closed by the flared wall.
  • the operation of the device is as follows.
  • This air flow is best used after it has swept the ribs, by sending it into the chamber 21 located immediately downstream, through the orifice 21a1 of the partition 21a, to participate in the blowing of the wall 20 of the transition channel.
  • the function of the valve is to isolate the chamber 19 of the enclosure 21 when the pressure P1 is less than P2.
  • the valve 30 is further advantageously configured, with a difference between the application surfaces of the pressures P1 and P2 so that it does not move from the closed position, that is to say the slide bearing against the flared portion with shutter, in the open position only when the pressure P1 is sufficiently greater than P2 to ensure stable operation.
  • the solution of the figure 3 comprises a central opening 33b which allows a limited circulation of the chamber 21 to the chamber 19 and ensures the pressurization of the latter.
  • the valve does not have a central orifice. It has in this case a single anti-return function.
  • the figure 4 shows a valve variant 130 with a cover 135 provided with projections 135b axial around the central opening 135a. These projections can limit the support surface of the slide. The other elements of the valve are not changed compared to that of the figure 3 .
  • the valve 230 differs from the previous by the slider 233 which is smaller in diameter than the diameter of the cylindrical portion of large diameter. It moves freely inside the latter.
  • the cover 235 has projections 235b as in the previous case. The air circulates around the slider and through the central bore 233b and then bypasses the axial projections 235b and passes through the central opening 235a of the cover 235.
  • the valve 330 comprises a slider 333 provided with notches 333b at its periphery leaving passages for air.
  • the flapper is also similar to the previous ones.
  • the valve 430 comprises a slider 433 with a portion 433c engaged in the portion 431a of small diameter of the tubular element 431.
  • This portion 433c comprises passages 433c1 for air.
  • the slider is also guided within the larger diameter portion 431c and includes openings 433a for the passage of air.
  • These openings 433a are peripherally so as to be closed by the flared portion 431b when the slide bears against it. These openings can be obtained by notches as shown on the figure 7 or be obtained by drilling.
  • valve variants The operation of these valve variants is the same as for the valve 30 of the figure 3 which they can substitute.
  • the geometry of these valves allows operation without seizure whatever the operating phase of the engine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
  • Sliding Valves (AREA)
EP09150354A 2008-01-11 2009-01-09 Gasturbinenmotor mit Ventil für die Verbindung von zwei Behältern Active EP2078822B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0800170A FR2926327B1 (fr) 2008-01-11 2008-01-11 Moteur a turbine a gaz avec clapet de mise en communication de deux enceintes

Publications (2)

Publication Number Publication Date
EP2078822A1 true EP2078822A1 (de) 2009-07-15
EP2078822B1 EP2078822B1 (de) 2012-07-18

Family

ID=40042795

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09150354A Active EP2078822B1 (de) 2008-01-11 2009-01-09 Gasturbinenmotor mit Ventil für die Verbindung von zwei Behältern

Country Status (6)

Country Link
US (1) US8221061B2 (de)
EP (1) EP2078822B1 (de)
JP (1) JP5210891B2 (de)
CA (1) CA2649399C (de)
FR (1) FR2926327B1 (de)
RU (1) RU2490475C2 (de)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10018067B2 (en) 2013-02-08 2018-07-10 General Electric Company Suction-based active clearance control system
US9598974B2 (en) * 2013-02-25 2017-03-21 Pratt & Whitney Canada Corp. Active turbine or compressor tip clearance control
FR3120090B1 (fr) * 2021-02-24 2024-06-21 Safran Aircraft Engines Turbine
US11970946B2 (en) * 2021-07-29 2024-04-30 General Electric Company Clearance control assembly
US11788425B2 (en) * 2021-11-05 2023-10-17 General Electric Company Gas turbine engine with clearance control system

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1082634A (en) * 1963-11-19 1967-09-06 Licentia Gmbh Improvements in or relating to sealing rings in turbines
US20050042080A1 (en) * 2003-08-06 2005-02-24 Snecma Moteurs Device for controlling clearance in a gas turbine
FR2906846A1 (fr) 2006-10-06 2008-04-11 Snecma Sa Canal de transition entre deux etages de turbine

Family Cites Families (12)

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Publication number Priority date Publication date Assignee Title
JPS58129037U (ja) * 1982-02-25 1983-09-01 三菱重工業株式会社 排気タ−ビン過給機のシ−リング装置
FR2540939A1 (fr) * 1983-02-10 1984-08-17 Snecma Anneau d'etancheite pour un rotor de turbine d'une turbomachine et installation de turbomachine munie de tels anneaux
US5127793A (en) * 1990-05-31 1992-07-07 General Electric Company Turbine shroud clearance control assembly
US5809772A (en) * 1996-03-29 1998-09-22 General Electric Company Turbofan engine with a core driven supercharged bypass duct
GB9715291D0 (en) * 1997-07-22 1997-09-24 T & N Technology Ltd Gasket
JP2003207071A (ja) * 2002-01-10 2003-07-25 Toshiba Corp 制御弁
US6851264B2 (en) * 2002-10-24 2005-02-08 General Electric Company Self-aspirating high-area-ratio inter-turbine duct assembly for use in a gas turbine engine
US7033133B2 (en) * 2003-12-10 2006-04-25 Honeywell International, Inc. Air turbine starter having a low differential check valve
JP4621553B2 (ja) * 2004-07-07 2011-01-26 株式会社東芝 蒸気弁および蒸気弁を備えた蒸気タービン
CN1746463B (zh) * 2004-09-08 2011-09-07 株式会社东芝 高温蒸汽阀和蒸汽轮机装置
RU2289759C1 (ru) * 2005-06-23 2006-12-20 Михаил Иванович Весенгириев Трубчатая камера сгорания газотурбинного двигателя
US7837436B2 (en) * 2007-05-25 2010-11-23 General Electric Company Method and apparatus for regulating fluid flow through a turbine engine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1082634A (en) * 1963-11-19 1967-09-06 Licentia Gmbh Improvements in or relating to sealing rings in turbines
US20050042080A1 (en) * 2003-08-06 2005-02-24 Snecma Moteurs Device for controlling clearance in a gas turbine
FR2906846A1 (fr) 2006-10-06 2008-04-11 Snecma Sa Canal de transition entre deux etages de turbine

Also Published As

Publication number Publication date
CA2649399A1 (fr) 2009-07-11
FR2926327A1 (fr) 2009-07-17
FR2926327B1 (fr) 2010-03-05
JP2009168022A (ja) 2009-07-30
EP2078822B1 (de) 2012-07-18
US20090180867A1 (en) 2009-07-16
RU2490475C2 (ru) 2013-08-20
RU2009100674A (ru) 2010-07-20
US8221061B2 (en) 2012-07-17
JP5210891B2 (ja) 2013-06-12
CA2649399C (fr) 2015-12-22

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