EP0261460A2 - Turbomachine avec des étages transsoniques - Google Patents

Turbomachine avec des étages transsoniques Download PDF

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Publication number
EP0261460A2
EP0261460A2 EP87112792A EP87112792A EP0261460A2 EP 0261460 A2 EP0261460 A2 EP 0261460A2 EP 87112792 A EP87112792 A EP 87112792A EP 87112792 A EP87112792 A EP 87112792A EP 0261460 A2 EP0261460 A2 EP 0261460A2
Authority
EP
European Patent Office
Prior art keywords
turbo machine
machine according
flow
impeller
hub
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
EP87112792A
Other languages
German (de)
English (en)
Other versions
EP0261460A3 (en
EP0261460B1 (fr
Inventor
Jean Dr. Hourmouziadis
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 GmbH
Original Assignee
MTU Motoren und Turbinen Union Muenchen 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 Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of EP0261460A2 publication Critical patent/EP0261460A2/fr
Publication of EP0261460A3 publication Critical patent/EP0261460A3/de
Application granted granted Critical
Publication of EP0261460B1 publication Critical patent/EP0261460B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/302—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor characteristics related to shock waves, transonic or supersonic flow

Definitions

  • the invention relates to a turbomachine with stages with transonic flow, in particular a gas turbine with a stationary guide vane.
  • the object of the invention is to achieve the abovementioned which occur in a turbomachine of the type mentioned at the beginning Eliminate disadvantages and in particular to prevent or minimize a circulating flow between the blades in each division on the trailing edge of the inlet grille.
  • the object is achieved in that a compensation device for pressure compensation of pressure gradients resulting from compression surges at the outlet edge of the preliminary grille is provided on the circumference behind the guide grille on the hub and / or housing.
  • the compensating device is preferably designed as at least one calming chamber, which extends over the circumference and is arranged on the hub side and has a circumferential opening towards the subsequent impeller, which is covered with a radially acting sealing flange of the impeller.
  • the sealing flange is expediently designed as a double peripheral seal, each of the two peripheral seals being designed as a labyrinth seal.
  • annular spaces arranged in the housing are formed with a connection to the main flow by means of a blocking element as a throttle point.
  • the annular space is filled with filling material such as metal or mineral wool, fiber, fabric, foam.
  • filling material such as metal or mineral wool, fiber, fabric, foam.
  • one or more compression surges 3 as shown in FIG. 1 occur at the trailing edge 18, particularly when the Mach number M is high. With the division t, these compression surges 3 generate periodic pressure gradients 4 which are many times larger than in the subsonic range.
  • annular spaces 14 there are annular spaces 14 in the area of the housing wall outside of the actual flow channel, then an inflow B into these annular spaces 14 takes place at points of high pressure, and an outflow D at points of low pressure, as can be seen in particular from FIG. 4 is. There is therefore a circulating flow C in each division at the radially outer and inner edge of the flow channel. As a result, the circulating gas at the edge of the Channel disturbs the main flow, increases the losses and deteriorates the efficiency of the gas turbine 1. In addition, the inflow of hot gas into the annular spaces 14 increases the temperature of the components, as a result of which the residual and thus the service life are reduced.
  • the invention proposes a pressure compensation device 2 for compensating the pressure gradients 4 created by compression surges 3 over the circumference behind the impeller 9 on the hub and / or housing 6, as can be seen in particular in FIGS. 5 and 6.
  • a calming chamber 8 which extends in the circumferential direction of the inlet grille 5 at a radially inner point with a circumferential opening to the rear to the subsequent impeller 9, the circumferential opening being covered with a radially oriented sealing flange 10 of the impeller 9 .
  • the sealing flange 10 is fastened to the impeller 9 via an axial flange 11 and provides a labyrinth seal 13 at the radially inner location and a labyrinth seal 12 at the radially outer location of the peripheral opening.
  • the circulating flow C takes place via the upper labyrinth seal 12.
  • the calming chamber 8 there is then a certain pressure compensation in the circumferential direction, which again makes it possible for the inflow of hot gas via the lower one with only a slightly increased back pressure in the interior 7 To prevent labyrinth seal 13.
  • the aforementioned pressure equalization device is found between the stationary and rotating part of the turbine.
  • the annular spaces 14 between standing parts are sealed against the main flow, with the aid of locking members 15, for example in the form of Angle profiles, which form the opening 16 as a throttle point.
  • the annular spaces 14 are filled with filling material 17, such as. B. metal or mineral wool, fiber, fabric, foam. Filling material 17 and locking member 15 nevertheless enable pressure equalization and temperature equalization in the annular space 14.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP87112792A 1986-09-20 1987-09-02 Turbomachine avec des étages transsoniques Expired - Lifetime EP0261460B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3632094 1986-09-20
DE19863632094 DE3632094A1 (de) 1986-09-20 1986-09-20 Turbomaschine mit transsonisch durchstroemten stufen

Publications (3)

Publication Number Publication Date
EP0261460A2 true EP0261460A2 (fr) 1988-03-30
EP0261460A3 EP0261460A3 (en) 1989-11-08
EP0261460B1 EP0261460B1 (fr) 1992-06-24

Family

ID=6310039

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87112792A Expired - Lifetime EP0261460B1 (fr) 1986-09-20 1987-09-02 Turbomachine avec des étages transsoniques

Country Status (4)

Country Link
US (1) US4836745A (fr)
EP (1) EP0261460B1 (fr)
DD (1) DD265444A1 (fr)
DE (2) DE3632094A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0710766A1 (fr) * 1994-11-05 1996-05-08 ROLLS-ROYCE plc Disque de rotor avec garniture d'étanchéité intégrée
US5721023A (en) * 1993-12-17 1998-02-24 E. I. Du Pont De Nemours And Company Polyethylene terephthalate articles having desirable adhesion and non-blocking characteristics, and a preparative process therefor

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2702242B1 (fr) * 1993-03-03 1995-04-07 Snecma Etage d'aubes libres à une extrémité.
DE4329014C1 (de) * 1993-08-28 1995-01-05 Mtu Muenchen Gmbh Rotorgehäuse, insbesondere Gehäuse für Turbotriebwerke

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB619722A (en) * 1946-12-20 1949-03-14 English Electric Co Ltd Improvements in and relating to boundary layer control in fluid conduits
DE2748597A1 (de) * 1976-11-01 1978-05-03 Gen Electric Ueberschallkompressor mit verbesserten betriebseigenschaften ausserhalb des bemessungsbetriebszustandes
US4164845A (en) * 1974-10-16 1979-08-21 Avco Corporation Rotary compressors
DE3127214A1 (de) * 1980-07-16 1982-03-25 Office National d'Etudes et de Recherches Aérospatiales, O.N.E.R.A., 92320 Châtillon-sous-Bagneux, Hauts-de-Seine "ueberschallverdichter"
FR2490722A1 (fr) * 1980-08-06 1982-03-26 Rolls Royce Joints d'etancheite a l'air pour turbomachines

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2427244A (en) * 1944-03-07 1947-09-09 Gen Electric Gas turbine
US2494328A (en) * 1946-03-22 1950-01-10 Gen Electric Axial flow elastic fluid turbine
US2897936A (en) * 1956-01-05 1959-08-04 Socony Mobil Oil Co Inc Moving bed flow control valve
GB979749A (en) * 1963-10-18 1965-01-06 Rolls Royce Axial flow compressors particularly for gas turbine engines
US4504188A (en) * 1979-02-23 1985-03-12 Carrier Corporation Pressure variation absorber
GB2111598B (en) * 1981-12-15 1984-10-24 Rolls Royce Cooling air pressure control in a gas turbine engine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB619722A (en) * 1946-12-20 1949-03-14 English Electric Co Ltd Improvements in and relating to boundary layer control in fluid conduits
US4164845A (en) * 1974-10-16 1979-08-21 Avco Corporation Rotary compressors
DE2748597A1 (de) * 1976-11-01 1978-05-03 Gen Electric Ueberschallkompressor mit verbesserten betriebseigenschaften ausserhalb des bemessungsbetriebszustandes
DE3127214A1 (de) * 1980-07-16 1982-03-25 Office National d'Etudes et de Recherches Aérospatiales, O.N.E.R.A., 92320 Châtillon-sous-Bagneux, Hauts-de-Seine "ueberschallverdichter"
FR2490722A1 (fr) * 1980-08-06 1982-03-26 Rolls Royce Joints d'etancheite a l'air pour turbomachines

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5721023A (en) * 1993-12-17 1998-02-24 E. I. Du Pont De Nemours And Company Polyethylene terephthalate articles having desirable adhesion and non-blocking characteristics, and a preparative process therefor
EP0710766A1 (fr) * 1994-11-05 1996-05-08 ROLLS-ROYCE plc Disque de rotor avec garniture d'étanchéité intégrée

Also Published As

Publication number Publication date
EP0261460A3 (en) 1989-11-08
DE3632094A1 (de) 1988-03-24
EP0261460B1 (fr) 1992-06-24
DE3779982D1 (de) 1992-07-30
US4836745A (en) 1989-06-06
DD265444A1 (de) 1989-03-01

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