EP2808559A1 - Ensemble structurel pour une turbomachine - Google Patents

Ensemble structurel pour une turbomachine Download PDF

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Publication number
EP2808559A1
EP2808559A1 EP14170068.2A EP14170068A EP2808559A1 EP 2808559 A1 EP2808559 A1 EP 2808559A1 EP 14170068 A EP14170068 A EP 14170068A EP 2808559 A1 EP2808559 A1 EP 2808559A1
Authority
EP
European Patent Office
Prior art keywords
flow path
main flow
assembly according
turbomachine
secondary flow
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
EP14170068.2A
Other languages
German (de)
English (en)
Other versions
EP2808559B1 (fr
Inventor
Volker Dr. Gümmer
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2808559A1 publication Critical patent/EP2808559A1/fr
Application granted granted Critical
Publication of EP2808559B1 publication Critical patent/EP2808559B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface

Definitions

  • the invention relates to a structural assembly for a turbomachine according to the preamble of patent claim 1.
  • turbomachines in particular of fluid flow machines such as fans, compressors, pumps and fans, is limited by the growth and separation of boundary layers in the rotor and stator tip region near the housing or hub wall. In the case of blade rows with a running gap, this leads to high secondary losses and possibly to the occurrence of operational instabilities at higher loads.
  • casing treatments As a countermeasure, it is known to use so-called casing treatments.
  • the simplest form of casing treatments are circumferential grooves of rectangular or parallelogram cross-section, such as in EP 0 754 864 A1 revealed and in the Fig. 1a outlined as an example.
  • Other solutions provide for rows of slots or openings in the housing, the individual slots / openings being oriented substantially in the flow direction and having a slender shape with a small extension viewed in the circumferential direction of the machine.
  • Such solutions are for example in the DE 101 35 003 C1 revealed and in the Fig. 1b outlined as an example.
  • a fluid flow machine which forms at least one secondary flow channel in the area of the blade leading edge in a main flow path boundary, which connects two openings arranged on the main flow path boundary.
  • Each secondary flow channel in each case connects a removal opening with a supply opening provided further upstream.
  • a spatially compact and robust structural design is to be provided.
  • the structural assembly has at least one support member and at least one insert member, wherein in the support member is provided a circumferentially extending recess which receives at least one insert member such that the support member, the at least one insert component largely on its not facing the main flow path sides surrounds, and wherein the insert member completely surrounds or forms at least one secondary flow channel.
  • the solution according to the invention implements the secondary flow channels in a separate component, the insert component, which is inserted into a recess or opening of the support component, which is for example part of the housing or the hub defining the main flow channel.
  • the invention contemplates a portion of the main flowpath of a turbomachine, in the region of a free end and nip row of blades, in which a series of circumferentially distributed secondary flow passages are provided.
  • the course of the secondary flow channels can each be spatially complex.
  • a structural assembly is provided for structurally implementing said secondary flow channels.
  • the insert component forms the main flow path boundary with at least part of its surfaces. It can further be provided that the insert component completely surrounds at least one secondary flow channel in such a way that all wetted surfaces of the secondary flow channel belong to the insert component undivided.
  • the support member is designed as an annular housing of a turbomachine and surrounds the support member, the at least one insert member from the outside.
  • the support member is formed as a half shell housing a turbomachine and the support member surrounds the at least one insert member from the outside.
  • the support member is annularly formed on the hub of a turbomachine and holds the support member, the at least one insert member from the inside.
  • the support member is formed semi-annular manner on the hub of a turbomachine and holds the support member, the at least one insert member from the inside.
  • the insert member may be formed according to the invention as a whole ring or as a ring sector.
  • the production of the insert component can be done for example by means of a casting, sintering or print manufacturing process.
  • An embodiment of the invention provides that the shape and the surfaces of the insert component are such that the insert member can be inserted into the support member in the axial direction of the turbomachine and an additional component in the axial direction adjacent to the support member and fixes the insert component. In this way, an otherwise required introduction of the insert component in the support member in the radial direction can be avoided.
  • An embodiment of the invention provides that on the insert component, which is designed as a ring sector or entire ring, on at least parts of its main flow path surface facing a Anstreifbelag is provided.
  • the insert component which is designed as a ring sector or entire ring
  • on at least parts of its main flow path surface facing a Anstreifbelag is provided.
  • it may also be provided that on the main flow path side facing the insert member adjacent to another whole or partial ring on which on at least parts of its main flow path surface facing a Anstreifbelag is provided.
  • the present invention relates generally to structural assemblies for turbomachinery such as turbines, and more particularly to fluid flow machines such as fans, compressors, pumps and fans, in both axial, semi-axial and radial designs.
  • the working medium or fluid may be gaseous or liquid.
  • the turbomachine may include one or more stages each having a rotor and a stator. In some cases, the stage is formed only by a rotor.
  • the rotor of a turbomachine in which a structural assembly according to the invention is used, consists of a number of blades, which are connected to the rotating shaft of the turbomachine and deliver energy to the working fluid in the case of the fluid flow machine.
  • the rotor can be designed with or without shroud on the outer blade end.
  • the stator of a turbomachine in which a structural assembly according to the invention is used, consists of a number of fixed blades, the hub side as the housing side can be designed with a fixed or free blade end.
  • the rotor drum and the blading are usually surrounded by a housing. In other cases, z. As in propellers or propellers, no housing exists.
  • a turbomachine in which a structural assembly according to the invention is used, can also have a stator in front of the first rotor, a so-called leading wheel. At least one stator or Vorleitrad - may be rotatably mounted - deviating from an immovable fixation - to change the angle of attack can. An adjustment is made for example by a spindle accessible from outside the annular channel.
  • a turbomachine in which a structural assembly according to the invention is used, have at least one row of adjustable rotors.
  • a turbomachine in which a structural assembly according to the invention is used in multi-stage have two opposing waves, so that the rotor blade rows change the direction of rotation from stage to stage. There are no stators between successive rotors.
  • a turbomachine in which a structural assembly according to the invention is used have a bypass configuration such that a single-flow annular channel behind a certain row of blades divides into two concentric annular channels, which in turn accommodate at least one more row of blades.
  • turbomachine in which a structural assembly according to the invention is used, it is, for example, a jet engine, in particular a turbofan engine.
  • the structural assembly is formed, for example, in the region of a compressor of a jet engine or turbofan engine.
  • the invention further relates to a fluid flow machine with a structural assembly according to the invention.
  • the Fig. 2A shows an arrangement of a blade row 3 with free end and running gap 5 in the meridian plane formed by the axial direction x and the radial direction r.
  • the nip 5 separates the blade tip from a component 2 belonging to the main flow path at the hub or housing of the fluid flow machine.
  • the component 2 forms a main flow path boundary 4 toward the main flow path.
  • the main flow direction in the main flow path is indicated by an arrow A. Upstream and / or downstream of the row of blades 3 with running gap, further rows of blades may be located.
  • a number of secondary flow channels 1 distributed on the circumference are provided in the region of the running gap 5, each of which forms an opening at its ends (feed opening and removal opening).
  • Fig. 2A shows the outline or the projection of a single secondary flow channel 1 in the meridian plane (xr).
  • xr meridian plane
  • each channel 1 has a three-dimensional spatially twisted course, which in the Fig. 2B is shown by way of example.
  • cross-sectional shape of the secondary flow channels 1 in the Fig. 2B merely exemplified as rectangular.
  • the cross section of the secondary flow channels 1 may be formed in other embodiments without corners, in particular circular or elliptical.
  • FIG. 3A shows a structural assembly according to the invention in the region of a row of blades with running gap in the meridian view (xr).
  • the main flow direction in the main flow path of the fluid flow machine in which the structural assembly is formed is indicated by the arrow A.
  • the blade row itself is not shown in favor of a simpler view.
  • At least one secondary flow channel 1 is formed, which has two openings 111, 112 in the main flow path boundary and is connected via this to the main flow path.
  • the secondary flow channel 1 is designed as a single-path path with an opening through which fluid flows from the main flow channel into the secondary flow channel and a second opening, through which the fluid leaves the secondary flow channel. Through which of the openings 111, 112 flows fluid and through which the openings 111, 112 fluid flows, depends on the exact positioning of the openings 111, 112 with respect to the blades of the blade row 3 (see. Fig. 2B ).
  • At least one of the secondary flow channels is formed by an arrangement in which a single channel is divided along its course into at least two subchannels, thereby forming a kind of "trouser configuration".
  • an inflow port and a plurality of outflow ports are included, which belong to the secondary flow passage.
  • the structural assembly comprises a support member 21 and an insert member 22.
  • a support member 21 Provided in the support member 21 is a circumferentially extending recess 210 which receives the insert member 22 along its circumference.
  • the insert member 22 (or, if multiple insert members are provided, each of the insert members) forms part of its surface with a portion of the outer main flow path boundary.
  • the liner member correspondingly forms at least a portion of its surfaces a portion of the inner major flow path boundary of the main flowpath of the fluid flow machine.
  • the insert member 22 in the insert member 22, and only in this, the secondary flow channel 1 is formed, that is, the insert member 22 completely surrounds the secondary flow channel 1, wherein all wetted surfaces of the secondary flow channel 1 and possibly further Sekundärströmungskanäle undividedly belong to the insert member 22 ,
  • the support member is designed as a ring housing of a turbomachine or as a half shell housing a turbomachine. With a corresponding arrangement in the hub region, it is, for example, annularly formed on the hub of a turbomachine or semi-annular on the hub of a turbomachine.
  • the insert component 22 is formed in one embodiment as a complete ring, which is inserted in the corresponding, extending in the circumferential direction recess 210 of the structural component 21.
  • the insert component 22 is designed as a ring sector. It can be provided that a plurality of secondary flow channels along the circumference of the main flow path boundary are realized, so that the insert member 22 in the circumferential direction forms a plurality of secondary flow channels 1.
  • the secondary flow channels 1 can be provided to produce the insert member 22 by means of a casting, sintering or print manufacturing process. It can be provided as explained, to produce the insert member 22 as a whole ring or as a ring sector with the said method.
  • FIGS. 3B shows a further embodiment of a structural assembly in the region of a row of blades with running gap in the meridian view (xr).
  • a recess 211 is formed in the support member 21 such that it does not surround the insert member 22 on all outer surfaces that are not part of the main flow path boundary.
  • a further additional component 23 is provided which is arranged in the axial direction (x) in front of the support component 21 and the insert component 22 and, for example, has a ring shape with a surface 230 facing the support component 21 and the insert component 22.
  • This arrangement makes it possible to insert the insert component 22 in a simple manner into the support component 21 in the axial direction (instead of in the radial direction as in the exemplary embodiment of FIG. 3A ) and then provide axial positioning by the accessory component 23.
  • the additional component 23 also forms surfaces that are part of the main flow path boundary.
  • the secondary flow channel 1 is completely formed in the insert component 22.
  • FIG. 3C shows a further variant of a structural assembly.
  • the embodiment differs from the embodiment of FIG. 3B in that additionally an abradable coating 6 is provided, which is formed directly on or in the insert component 22, it being possible to provide that at least one of the openings 111, 112 of the secondary flow channel 1 is located in an area in which the abradable coating 6 is formed , It can be provided that the abradable coating 6 is formed as a ring sector or entire ring on the insert member 22 and thereby provides a main flow path facing surface. Such a squish coating serves to mesh with the blades 3 of a rotating blade row and to achieve that the running gap 5 can be minimized (see. Fig. 2A ).
  • the Figure 3D shows a further embodiment of a structural assembly.
  • the abradable coating 6 is formed in an intermediate ring 7, which is inserted into a corresponding recess 220 in the insert member 22.
  • the additional ring 7 can be formed as a whole ring or as a partial ring.
  • the abradable coating 6 is provided on its surface facing the main flow path.
  • FIGS. 3A . 3B . 3C . 3D are described, combined with each other.
  • a further variant of the invention provides that an abradable coating 6 also in the embodiment of Fig. 3A is realized.
  • the invention is not limited in its embodiment to the embodiments shown above, which are to be understood only as examples.
  • shape and configuration of the secondary flow channels and the support member and the insert member may be realized in a different manner than shown.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP14170068.2A 2013-05-31 2014-05-27 Ensemble structurel pour une turbomachine Active EP2808559B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102013210169.4A DE102013210169A1 (de) 2013-05-31 2013-05-31 Strukturbaugruppe für eine Strömungsmaschine

Publications (2)

Publication Number Publication Date
EP2808559A1 true EP2808559A1 (fr) 2014-12-03
EP2808559B1 EP2808559B1 (fr) 2017-10-11

Family

ID=50842105

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14170068.2A Active EP2808559B1 (fr) 2013-05-31 2014-05-27 Ensemble structurel pour une turbomachine

Country Status (3)

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US (1) US10006467B2 (fr)
EP (1) EP2808559B1 (fr)
DE (1) DE102013210169A1 (fr)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2818724B1 (fr) * 2013-06-27 2020-09-23 MTU Aero Engines GmbH Turbomachine et procédé
EP3081779A1 (fr) * 2015-04-14 2016-10-19 MTU Aero Engines GmbH Élément de canal d'écoulement de compresseur de turbine à gaz
GB201719665D0 (en) * 2017-11-27 2018-01-10 Univ Leicester A flow assembly for an axial turbomachine
DE102018116062A1 (de) * 2018-07-03 2020-01-09 Rolls-Royce Deutschland Ltd & Co Kg Strukturbaugruppe für einen Verdichter einer Strömungsmaschine
US11473438B2 (en) * 2019-06-04 2022-10-18 Honeywell International Inc. Grooved rotor casing system using additive manufacturing method
FR3107917B1 (fr) * 2020-03-04 2022-09-09 Safran Carter de roue mobile pour turbomachine
FR3122450B1 (fr) 2021-04-28 2023-05-12 Safran Ensemble de turbomachine comprenant un carter et un support de traitement aerodynamique en tete d’aubes et turbomachine correspondante
US11732612B2 (en) * 2021-12-22 2023-08-22 Rolls-Royce North American Technologies Inc. Turbine engine fan track liner with tip injection air recirculation passage
US11702945B2 (en) 2021-12-22 2023-07-18 Rolls-Royce North American Technologies Inc. Turbine engine fan case with tip injection air recirculation passage
US11946379B2 (en) 2021-12-22 2024-04-02 Rolls-Royce North American Technologies Inc. Turbine engine fan case with manifolded tip injection air recirculation passages
US12258870B1 (en) 2024-03-08 2025-03-25 Rolls-Royce North American Technologies Inc. Adjustable fan track liner with slotted array active fan tip treatment for distortion tolerance
US12215712B1 (en) 2024-05-09 2025-02-04 Rolls-Royce North American Technologies Inc. Adjustable fan track liner with dual grooved array active fan tip treatment for distortion tolerance
US12286936B1 (en) 2024-05-09 2025-04-29 Rolls-Royce North American Technologies Inc. Adjustable fan track liner with groove array active fan tip treatment for distortion tolerance
US12209541B1 (en) 2024-05-09 2025-01-28 Rolls-Royce North American Technologies Inc. Adjustable fan track liner with dual slotted array active fan tip treatment for distortion tolerance
US12209502B1 (en) 2024-06-28 2025-01-28 Rolls-Royce North American Technologies Inc. Active fan tip treatment using rotating drum array with axial channels in fan track liner for distortion tolerance
US12168983B1 (en) 2024-06-28 2024-12-17 Rolls-Royce North American Technologies Inc. Active fan tip treatment using rotating drum array in fan track liner with axial and circumferential channels for distortion tolerance

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EP0497574A1 (fr) 1991-01-30 1992-08-05 United Technologies Corporation Virole avec canaux de récirculation pour soufflante
EP0751280A1 (fr) * 1995-05-31 1997-01-02 United Technologies Corporation Paroi avec plenum pour l'alignement de l'écoulement dans les aubes de compresseur
EP0754864A1 (fr) 1995-07-18 1997-01-22 Ebara Corporation Turbomachine
US5950308A (en) * 1994-12-23 1999-09-14 United Technologies Corporation Vaned passage hub treatment for cantilever stator vanes and method
DE10135003C1 (de) 2001-07-18 2002-10-02 Mtu Aero Engines Gmbh Verdichtergehäusestruktur
EP1286022A1 (fr) * 2001-08-14 2003-02-26 United Technologies Corporation Traitement de l'enveloppe pour compresseurs
DE10330084A1 (de) 2002-08-23 2004-03-04 Mtu Aero Engines Gmbh Rezirkulationsstruktur für Turboverdichter
US20050226717A1 (en) 2004-04-13 2005-10-13 Rolls-Royce Plc Flow control arrangement
EP1659293A2 (fr) * 2004-11-17 2006-05-24 Rolls-Royce Deutschland Ltd & Co KG Turbomachine
DE102008037154A1 (de) 2008-08-08 2010-02-11 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine

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DE102004030597A1 (de) * 2004-06-24 2006-01-26 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Aussenradstrahlerzeugung am Stator
DE102004032978A1 (de) * 2004-07-08 2006-02-09 Mtu Aero Engines Gmbh Strömungsstruktur für einen Turboverdichter
DE102008017844A1 (de) 2008-04-08 2009-10-15 Rolls-Royce Deutschland Ltd & Co Kg Strömungsmaschine mit Fluid-Injektorbaugruppe
DE102008019603A1 (de) * 2008-04-18 2009-10-22 Rolls-Royce Deutschland Ltd & Co Kg Strömungsmaschine mit schaufelreiheninterner Fluid-Rückführung
EP2639411B1 (fr) * 2012-03-12 2014-12-10 MTU Aero Engines GmbH Boîtier de turbomachine avec un système de recirculation de fluide

Patent Citations (11)

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Publication number Priority date Publication date Assignee Title
EP0497574A1 (fr) 1991-01-30 1992-08-05 United Technologies Corporation Virole avec canaux de récirculation pour soufflante
US5950308A (en) * 1994-12-23 1999-09-14 United Technologies Corporation Vaned passage hub treatment for cantilever stator vanes and method
EP0751280A1 (fr) * 1995-05-31 1997-01-02 United Technologies Corporation Paroi avec plenum pour l'alignement de l'écoulement dans les aubes de compresseur
EP0754864A1 (fr) 1995-07-18 1997-01-22 Ebara Corporation Turbomachine
DE10135003C1 (de) 2001-07-18 2002-10-02 Mtu Aero Engines Gmbh Verdichtergehäusestruktur
EP1286022A1 (fr) * 2001-08-14 2003-02-26 United Technologies Corporation Traitement de l'enveloppe pour compresseurs
US6585479B2 (en) 2001-08-14 2003-07-01 United Technologies Corporation Casing treatment for compressors
DE10330084A1 (de) 2002-08-23 2004-03-04 Mtu Aero Engines Gmbh Rezirkulationsstruktur für Turboverdichter
US20050226717A1 (en) 2004-04-13 2005-10-13 Rolls-Royce Plc Flow control arrangement
EP1659293A2 (fr) * 2004-11-17 2006-05-24 Rolls-Royce Deutschland Ltd & Co KG Turbomachine
DE102008037154A1 (de) 2008-08-08 2010-02-11 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine

Also Published As

Publication number Publication date
EP2808559B1 (fr) 2017-10-11
US20150086344A1 (en) 2015-03-26
DE102013210169A1 (de) 2014-12-04
US10006467B2 (en) 2018-06-26

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