EP1739283A2 - Joint d'étanchéité ajustable entourant les extrémités des aubes d'une turbomachine - Google Patents

Joint d'étanchéité ajustable entourant les extrémités des aubes d'une turbomachine Download PDF

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Publication number
EP1739283A2
EP1739283A2 EP06012930A EP06012930A EP1739283A2 EP 1739283 A2 EP1739283 A2 EP 1739283A2 EP 06012930 A EP06012930 A EP 06012930A EP 06012930 A EP06012930 A EP 06012930A EP 1739283 A2 EP1739283 A2 EP 1739283A2
Authority
EP
European Patent Office
Prior art keywords
rotor
rotor gap
control device
gap
unit
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.)
Withdrawn
Application number
EP06012930A
Other languages
German (de)
English (en)
Other versions
EP1739283A3 (fr
Inventor
André Werner
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1739283A2 publication Critical patent/EP1739283A2/fr
Publication of EP1739283A3 publication Critical patent/EP1739283A3/fr
Withdrawn legal-status Critical Current

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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
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2270/00—Control
    • F05D2270/60—Control system actuates means
    • F05D2270/65—Pneumatic actuators
    • 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
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F05D2300/431—Rubber
    • 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
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F05D2300/437—Silicon polymers
    • 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
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity

Definitions

  • the invention relates to a rotor gap control device for a compressor of a turbomachine, in particular a flight drive, which has a rotor and a rotor surrounding the rotor to form a rotor gap housing, wherein the rotor gap control device has a movable into the rotor gap sealing element and an actuator unit.
  • the rotor gap between the stationary rotor housing and rotating rotor is a source of flow losses and thus a cause of reduced efficiency.
  • the flow losses occur on the one hand by vortex formation and flow separation in or at the rotor gap , which also leads to increased flow noise, on the other hand by a compensation flow, which is directed against the main flow direction by the rotor and limits the achievable pressure difference between the high pressure side and the low pressure side of the turbomachine.
  • a rotor gap would not exist. In practice, however, this is not possible, since in this case the tips of the rotor blades touch the housing and would grind on rotation of the rotor on the housing and thus wear.
  • This problem is particularly pronounced in turbomachines in which the rotors rotate at high speed and / or are exposed to high temperatures, such as in aircraft engines and gas turbines and exhaust gas turbochargers.
  • the rotor blade lengthens depending on the temperature and the speed.
  • the housing expands depending on the operating temperature. Through the rotor gap, the expansion of the housing and the elongation of the rotor blades are compensated, without it being possible for the turbomachine to be damaged.
  • the width of the rotor gap and thus the losses of the turbomachine consequently change as a function of the rotational speed and the temperature in the operating state just passed through.
  • the rotor gap is usually adjusted so that in a continuous operating point, in which the turbomachine is usually operated, the smallest possible rotor gap is present.
  • this continuous operating point is, for example, at cruising speed.
  • limit load ranges and start-up ranges of the turbomachine are taken into account in the design of the pipe gap in practice:
  • the rotor gap should be dimensioned so that damage to the rotor blade and housing can be avoided even under extreme conditions with acceptable flow losses.
  • a pressure chamber is provided behind the housing wall, which extends over a plurality of rotor and stator rows. Applying low pressure or high pressure to the pressure chamber prevents the rotor blades from rubbing against the housing wall during start-up operations.
  • the device of US 5,781,333 has housing segments, which are moved over an admission of pressure chambers with compressed air in the direction of the rotor blades. To increase the response, the pressure chamber is provided with vent valves for quick pressure equalization.
  • a rotor gap control module for a flow machine with a rotor and a housing which surrounds the rotor to form a rotor gap.
  • the rotor gap control module is provided with an actuator unit which acts on a sealing element and moves it into or out of the rotor gap.
  • the sealing element is smaller than the distance between two successive rotor blades.
  • the disadvantage here is that many actuators are needed and that the gap control module is interrupted.
  • the invention is therefore an object of the invention to improve the aforementioned rotor gap control devices for use in compressors accordingly.
  • operational degradation due to erosion, aging, etc. is to be counteracted.
  • the efficiency should be maintained and the surge margin maintained.
  • the sealing element is formed as a circumferential inlet lining of flexible, rubber-like material in which at least one likewise circumferential tubular membrane is arranged, which is acted upon by the actuator unit with pressurized fluid.
  • Three tubular membranes have proven to be advantageous, the central membrane having a circular cross section and the two outer tubular membranes having an oval cross section.
  • the design of the inlet lining of flexible material ensures that non-uniform expansions can be compensated without damage to the blading. In this case, the material of the inlet lining is simply removed at certain points by the blades, without any damage to the blades.
  • an advantageous development of the invention provides that the inlet lining is received in a circumferential recess in the compressor housing. This recess can be removed, for example, in a machining process from the housing inner wall.
  • a further advantageous embodiment of the invention provides that the inlet lining is made of silicone rubber.
  • Silicone rubber has good physical material properties. So silicone rubber can be used for a long time at temperatures up to 140 ° C, at times even at temperatures up to 270 ° C. Silicone polymers are characterized in particular by a high temperature stability and excellent elasticity in a range of -50 ° C to 270 ° C.
  • the actuator unit is designed as a pneumatic adjustment unit, which acts on the at least one tube membrane.
  • the Aktuatoreineit can be designed as a control valve for the supply of compressor exhaust air.
  • a further advantageous embodiment of the invention provides that a control unit is provided for compressed air control. In this way, the amount of compressed air of the actual gap width can be adjusted, which allows a higher accuracy than the departure of pre-stored gap width curves.
  • a further advantageous development of the invention provides that a sensor unit connected to the control unit is provided for measuring the rotor gap (8). As a result, the control unit can be supplied with a feedback signal.
  • FIG. 1 shows a schematic half section through an axially traversed aircraft engine 1 with a compressor and a rotor gap control device.
  • FIG. 2 shows a schematic detail section through an embodiment according to the invention of a rotor gap control device 2.
  • a compressor housing 3 rotates a compressor rotor with compressor blades 4.
  • a circumferential recess 11 is incorporated in the compressor housing 3, in which a circumferential inlet lining 5 is made of silicone rubber.
  • the circumferential inlet lining 5 with a substantially rectangular cross-section has in the interior a central tubular membrane 6 with a round cross section and two outer tubular membranes 7 with an oval cross section.
  • the flow channel 9 facing side of the inlet lining 5 closes in the unactuated state with the housing inner wall 10 and occurs only when actuated beyond this, as shown in Figure 2.
  • a rotor gap 8 is formed between the compressor housing 3 and the compressor blade 4.
  • This rotor gap 8 is different depending on the operating point of the turbomachine, part load, full load, or similar.
  • By controlled pneumatic actuation of the tube membranes 6, 7 of the inlet lining 5 is extended accordingly and moved into the rotor gap 8 until the rotor gap 8 disappears.
  • the invention is not limited in its execution to the above-mentioned preferred embodiment. Rather, a number of variants are conceivable, which make use of the illustrated solution even with fundamentally different types of execution.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP06012930.1A 2005-06-30 2006-06-23 Joint d'étanchéité ajustable entourant les extrémités des aubes d'une turbomachine Withdrawn EP1739283A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102005030426A DE102005030426A1 (de) 2005-06-30 2005-06-30 Rotorspalt Steuervorrichtung für einen Verdichter

Publications (2)

Publication Number Publication Date
EP1739283A2 true EP1739283A2 (fr) 2007-01-03
EP1739283A3 EP1739283A3 (fr) 2013-05-08

Family

ID=36675186

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06012930.1A Withdrawn EP1739283A3 (fr) 2005-06-30 2006-06-23 Joint d'étanchéité ajustable entourant les extrémités des aubes d'une turbomachine

Country Status (3)

Country Link
US (1) US7654791B2 (fr)
EP (1) EP1739283A3 (fr)
DE (1) DE102005030426A1 (fr)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0910070D0 (en) * 2009-06-12 2009-07-22 Rolls Royce Plc System and method for adjusting rotor-stator clearance
DE102010023998A1 (de) 2010-06-16 2011-12-22 Mtu Aero Engines Gmbh Strömungskanal mit veränderlicher Kanalgeometrie
GB201021327D0 (en) 2010-12-16 2011-01-26 Rolls Royce Plc Clearance control arrangement
US8973373B2 (en) 2011-10-31 2015-03-10 General Electric Company Active clearance control system and method for gas turbine
US9234435B2 (en) 2013-03-11 2016-01-12 Pratt & Whitney Canada Corp. Tip-controlled integrally bladed rotor for gas turbine
WO2015094622A1 (fr) 2013-12-17 2015-06-25 United Technologies Corporation Système de commande d'espacement de pale de machine à turbine
US10458429B2 (en) 2016-05-26 2019-10-29 Rolls-Royce Corporation Impeller shroud with slidable coupling for clearance control in a centrifugal compressor
GB2553806B (en) 2016-09-15 2019-05-29 Rolls Royce Plc Turbine tip clearance control method and system
US10753223B2 (en) 2017-10-04 2020-08-25 General Electric Company Active centering control for static annular turbine flowpath structures
US10724535B2 (en) * 2017-11-14 2020-07-28 Raytheon Technologies Corporation Fan assembly of a gas turbine engine with a tip shroud
CN108775850B (zh) * 2018-06-11 2024-01-19 中国空气动力研究与发展中心高速空气动力研究所 一种可连续变叶顶间隙的平面叶栅试验装置及其试验方法

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2922835A1 (de) * 1979-06-06 1980-12-18 Motoren Turbinen Union Umfangsspaltdichtung an axialstroemungsmaschinen
GB2195715A (en) * 1986-10-08 1988-04-13 Rolls Royce Plc Rotor blade tip-shroud
US5211534A (en) * 1991-02-23 1993-05-18 Rolls-Royce Plc Blade tip clearance control apparatus
US5344284A (en) * 1993-03-29 1994-09-06 The United States Of America As Represented By The Secretary Of The Air Force Adjustable clearance control for rotor blade tips in a gas turbine engine
DE10117231A1 (de) * 2001-04-06 2002-10-31 Hodson Howard Rotorspalt-Steuermodul
DE10244038A1 (de) * 2002-09-21 2004-04-01 Mtu Aero Engines Gmbh Einlaufbelag für Axialverdichter von Gasturbinen, insbesondere von Gasturbinentriebwerken

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4135851A (en) * 1977-05-27 1979-01-23 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Composite seal for turbomachinery
US4247247A (en) * 1979-05-29 1981-01-27 General Motors Corporation Blade tip clearance control
US4422827A (en) * 1982-02-18 1983-12-27 United Technologies Corporation Blade root seal
GB2169962B (en) * 1985-01-22 1988-07-13 Rolls Royce Blade tip clearance control
US5248224A (en) * 1990-12-14 1993-09-28 Carrier Corporation Orificed shroud for axial flow fan
US5203673A (en) * 1992-01-21 1993-04-20 Westinghouse Electric Corp. Tip clearance control apparatus for a turbo-machine blade
GB2313414B (en) * 1996-05-24 2000-05-17 Rolls Royce Plc Gas turbine engine blade tip clearance control

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2922835A1 (de) * 1979-06-06 1980-12-18 Motoren Turbinen Union Umfangsspaltdichtung an axialstroemungsmaschinen
GB2195715A (en) * 1986-10-08 1988-04-13 Rolls Royce Plc Rotor blade tip-shroud
US5211534A (en) * 1991-02-23 1993-05-18 Rolls-Royce Plc Blade tip clearance control apparatus
US5344284A (en) * 1993-03-29 1994-09-06 The United States Of America As Represented By The Secretary Of The Air Force Adjustable clearance control for rotor blade tips in a gas turbine engine
DE10117231A1 (de) * 2001-04-06 2002-10-31 Hodson Howard Rotorspalt-Steuermodul
DE10244038A1 (de) * 2002-09-21 2004-04-01 Mtu Aero Engines Gmbh Einlaufbelag für Axialverdichter von Gasturbinen, insbesondere von Gasturbinentriebwerken

Also Published As

Publication number Publication date
US7654791B2 (en) 2010-02-02
DE102005030426A1 (de) 2007-01-04
US20090317228A1 (en) 2009-12-24
EP1739283A3 (fr) 2013-05-08

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