CN103080562A - Turbojet casing and turbojet receiving such casings - Google Patents

Turbojet casing and turbojet receiving such casings Download PDF

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Publication number
CN103080562A
CN103080562A CN2011800425646A CN201180042564A CN103080562A CN 103080562 A CN103080562 A CN 103080562A CN 2011800425646 A CN2011800425646 A CN 2011800425646A CN 201180042564 A CN201180042564 A CN 201180042564A CN 103080562 A CN103080562 A CN 103080562A
Authority
CN
China
Prior art keywords
housing
blade
attachment
tail edge
preceding limb
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.)
Pending
Application number
CN2011800425646A
Other languages
Chinese (zh)
Inventor
P·邓里维
R·梅森
B·德茹瓦约
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 Nacelles SAS
Safran Landing Systems SAS
Original Assignee
Messier Bugatti Dowty SA
Aircelle SA
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 Messier Bugatti Dowty SA, Aircelle SA filed Critical Messier Bugatti Dowty SA
Publication of CN103080562A publication Critical patent/CN103080562A/en
Pending 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials 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
    • 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
    • F04D29/542—Bladed diffusers
    • 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
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • 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
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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

Abstract

The invention relates to a turbojet casing adapted to receive a plurality of blades and comprising means for attaching one end of each blade to the casing (21, 30). The invention is characterised in that the attachment means extend over a surface of the casing opposite the blades, and the casing comprises holes (26) for the passage of the ends of the blades, such that the latter can engage with the attachment means of the casing. The invention also relates to a turbojet comprising such a casing.

Description

The turbo jet engine of turbojet engine housing and this kind of admittance housing
Technical field
The present invention relates to a kind of turbojet engine housing that is suitable for admitting a plurality of blades, and relate to a kind of turbo jet engine that holds this kind housing.
Background technique
Known toroidal shell has the attachment that cooperates for the end of blade.
Various attachments have been proposed.For example, document US 2009/0317246 recommends to form the end of cylindrical bar, and it forms the part of external casing and carries two fastening piece flanks, causes thus manufacturing very complicated shape.Document US 2009/0317246 is recommended in before the assembly of will be in this way making is installed in the housing, by circular ring blade is linked together, and this scheme implements complicated and needs assembling tool.
Summary of the invention
Therefore, the objective of the invention is to propose the simple and easy-to-install turbojet engine housing of a kind of manufacturing.
For this reason, the invention provides a kind of turbojet engine housing that is suitable for admitting a plurality of blades, this housing comprises the attachment that an end of each blade is attached to housing.According to the present invention, attachment extends at the face towards away from blade of housing, and housing comprises the hole that allows blade tip pass through, thereby they can cooperate with the attachment of housing.
This kind structure can obtain to make simple and easy-to-install housing.
In a preferred embodiment, attachment comprises the annular construction member that extends around housing, this housing comprises long fibre and thermoplastic resin, annular construction member obtains by pultrusion, and be impregnated with thermoplastic resin, the thermoplastic resin of this thermoplastic resin and housing carries out heat sealing, by hot compression assembly is linked together.This produces the assembly with strong cohesive force.
The present invention also provides the turbo jet engine that comprises at least one housing of the present invention and a plurality of blades, and each blade has an end that is connected to housing.
Preferably, in this turbo jet engine, each blade comprises:
Elongated single-piece is anterior, and it cuts from having with the resin bonded fiber and forming the pultrusion section structural member of preceding limb;
Elongated single-piece rear portion, it cuts from having with the resin bonded fiber and forming the pultrusion section structural member of tail edge;
Epidermis, it cuts from the fabric that is impregnated with resin and extends to cover the side of inner core, and covers at least the preceding limb that adjoins with core and the zone of tail edge;
In preceding limb and the tail edge at least one has at least an end place at blade from the outstanding extension of inner core, so that the attachment that carrying is used for attached blade and cooperates with the attachment of turbojet engine housing.
Description of drawings
Read following description to specific embodiment of the present invention with reference to accompanying drawing, will be appreciated that other features and advantages of the present invention, in the accompanying drawing:
Fig. 1 is the planimetric map that is designed to be fastened to the blade of housing of the present invention;
Fig. 2 is the stereogram of Fig. 1 blade, and the epidermis that covers the blade inner core is partly cut;
Fig. 3 is the stereogram that blade is fastened to the first technology of housing of the present invention; And
Fig. 4 is the stereogram that blade is fastened to the second technology of housing of the present invention.
Embodiment
With reference to Fig. 1 and 2, wherein illustrated blade 1 is the guide vane that extends in the fan of turbo jet engine.In this embodiment, blade 1 has the preceding limb 2 that is single-piece slim-lined construction form.Blade 1 also has tail edge 3, and this tail edge is single-piece slim-lined construction form equally.
From obtain by pultrusion and preferably cut out preceding limb 2 and tail edge 3(so-called " pulling braiding (pullbraiding) " method tilted-putted section member of fiber).This section member has fiber (for example, carbon fiber), and axis arranged along the longitudinal basically is in order to form elongated body.Be ideally, basically 80% of fiber arrange along the longitudinal axis X of preceding limb and along the longitudinal axis Y of tail edge, and fiber 20% become the inclination angles of about 60 degree to arrange with respect to longitudinal axis.This kind layout of such ratio and fiber only provides for example.Fiber impregnation is in thermoplastic resin.
Inner core 4 extends between preceding limb 2 and tail edge 3.Epidermis 5 is comprised of two flank (web) 5A and 5B in this example, they obtain by cutting from the fabric of pre-impregnated resin, flank extends in the both sides of inner core 4, with the preceding limb 2 that covers inner core and adjoin with inner core 4 and the zone 6,7 of tail edge 3.
The face that is not covered by flank 5A and 5B of inner core 4 has formed the free end of inner core 4, in this example, and by short fibre be inserted in 22 protections of resin blend thing and reinforcement free end in the inner chamber that the free edge by flank 5A and 5B and inner core 4 forms.Preceding limb 2 and tail edge 3 comprise extension 10,11,12 and 13, and they are outstanding and in each end extension of blade 1 from inner core 4.
The all parts of blade 1 fits together by hot compression, thereby each parts of assembly are connected to each other.The assembling of the type gives blade 1 very large intensity on the whole.
At last, hole 14,15,16 and 17 is formed in the extension 10,11,12 and 13, the extension being converted to the device of attached blade 1, the complementary attachment device that this device is designed in the housing with turbo jet engine cooperates, as following describe in detail with reference to Fig. 3 and 4.
Fig. 3 illustrates the first technology that blade 1 is fastened to annular turbine jet plane housing 20.(this illustrates the frame of turbo jet engine, and it is made by the long fibre that is impregnated with thermoplastic resin.) housing 20 has allows the holes 26 of extension 10 and 12 by housing 20 of preceding limb 2 and tail edge 3.Hole 26 is shown as enough sizes, to allow passing through same hole from the extension of preceding limb and tail edge.Yet, in a kind of variant, the hole can be divided into two parts, comprise the upstream orifice and the downstream aperture that allow respectively preceding limb and tail edge pass through.
Housing 20 is fitted with the device for attached preceding limb, and this device is the form of peripheral tracks 21, and peripheral tracks 21 is being extended towards the face away from blade around housing.Track 21 forms the shell of the head 24 that is suitable for admitting fastener element 23, and head is roughly T-shaped or L shaped.One of these elements show in the drawings.
Fastener element 23 has the opposite end 25 away from its head 24, and this opposite end cuts into the extension 10 of admitting preceding limb.In this example, fastener element 23 usefulness pins are connected to extension 10.For this purpose, end 25 comprises that the hole 14 in the extension 10 that is positioned to preceding limb 2 aligns in order to admit the hole (not shown) of fastener pin 27.
By the second track 21 ' in a similar manner fixedly extension 12, the second fastener elements 23 ' of tail edge 3 be engaged in the second track 21 ', to cooperate with the extension 12 of tail edge 3, by means of pin 27 ' with the assembly pin joint together.
In a preferred embodiment, track 21 and 21 ' and fastener element 23 and 23 ' make by pultrusion, and be impregnated with thermoplastic resin, thereby by the single hot compression operation on housing 20, whole assembly linked together.
In addition, Fig. 3 only illustrates half of blade 1. Unshowned terminal part 11 and 13 is fastened to inner housing in the same manner as described above.Yet if blade does not have structure function, blade need to be fastened to only housing.
Fig. 4 illustrates for the second technology that blade 1 is fastened to turbojet engine housing 20.In the figure, attachment comprises around the angle section 30 of housing in peripheral disposition.This angle section 30 extends at the face towards away from blade 1 of housing 20.Housing 20 has through hole 26, to allow the preceding limb of blade and the extension of tail edge pass through housing 20, so that they are towards angle section 30.
In better mode, angle section 30 is made by pultrusion, and is impregnated with thermoplastic resin.
Angle section 30 has L shaped cross section, and it has first surface 28 and second 29, and first surface 28 is fastened to housing 20 by hot compression, and second 29 usefulness pin is fastened to extension 10.For this purpose, the face 29 of angle section 30 is punched a hole, aligns with the hole 114 in the extension 10 that is formed on preceding limb in this hole.Also should observe, hole 114 is vertically formed with respect to the hole 14 of above-described embodiment.Also should observe, extension 10 presents straight face after processing, and this face is resisted against the opposed face of bead 29.
As in the above-mentioned example, the various elements of housing link together by hot compression.
In addition, the preceding limb 2 that not yet shows and the extension 11 of tail edge 3,12 with 13 with fastening like the identical mode of angle steel with respective class.
To all blades that will install, repeat blade 1 is fastened to the operation of angle section 30.
Except the effect by the fastening blade in extension of its preceding limb or tail edge, should see that track and angle section also help the rigidity of reinforcing the turbojet engine housing.
Nature, the present invention is not limited to above-described embodiment, and these embodiments can stand the various variations that those skilled in the art understand, and can not surmount by scope of the present invention as defined in the claims.
Especially, for the manufacture of the various elements 2,3 of blade 1,4 and 5 and for the manufacture of attachment 21,23,27 material, can be composite material or metallic material or their combination equally.
Similarly, the free-ended reinforcer 22 of visible covering inner core 4 among Fig. 2, one or two the epidermis that turned down replaces among available flank 5A, the 5B, or is associated with epidermis.In situation so, the size of flank 5A, 5B should be adjusted and reserve and be suitable for covering the free-ended flap of inner core.
Similarly, the attachment of the attachment of housing and preceding limb and tail edge can link together by means of operation, these operations comprise hot compression, welding, bonding, or use nut-bolt fastener, or are used for any other technological scheme that element is fixed together.
In addition, blade can have and is different from above-mentioned structure, for example individual construction.
At last, although Fig. 3 with 4 in two different embodiments each extension 10,11,12,13 to preceding limb 2 and tail edge 3 identical attachment means has been proposed, but to being fastened to each extension of housing 20, use in the attachment means one or the other with independent mode, this and the present invention do not run counter to.
Although comprising, the attachment of describing in the literary composition is around the track of housing extension or the annular construction member of peripheral angle section form, but also can consider other attachment, such as the fastening piece lug, by after the housing, their end is fastened to this fastening piece lug at blade.

Claims (7)

1. turbojet engine housing that is suitable for admitting a plurality of blades, this housing comprises the attachment (21,30) that an end of each blade is attached to housing, this housing is characterised in that, attachment extends at the face towards away from blade of housing, housing comprises the hole (26) that allows blade tip pass through, thereby they can cooperate with the attachment of housing.
2. housing as claimed in claim 1 is characterized in that, described attachment comprises the annular construction member (21,30) that extends around housing.
3. housing as claimed in claim 2 is characterized in that, described annular construction member comprises that at least one has the peripheral tracks of the end of fastener element (23) (24) (21), is used for the fastening end that is inserted in blade wherein.
4. housing as claimed in claim 2 is characterized in that, described annular construction member comprises peripheral angle section (30), and the end of blade directly is fastened to peripheral angle section.
5. housing as claimed in claim 2, it is characterized in that, described housing is made by the long fibre that is associated with thermoplastic resin, and annular construction member (21,30) obtains by pultrusion, and be impregnated with thermoplastic resin, the thermoplastic resin of this thermoplastic resin and housing carries out heat sealing, by hot compression described assembly is linked together.
6. a turbo jet engine comprises that each blade has an end that is connected to housing such as described at least one housing of any aforementioned claim and a plurality of blade.
7. turbo jet engine as claimed in claim 6 is characterized in that, each blade comprises:
Elongated single-piece anterior (2), it cuts from having with the resin bonded fiber and forming the pultrusion section structural member of preceding limb;
Elongated single-piece rear portion (3), it cuts from having with the resin bonded fiber and forming the pultrusion section structural member of tail edge;
Form the core (4) of inner core, between preceding limb (2) and tail edge (3), extend; And
Epidermis (5), it cuts from the fabric that is impregnated with resin and extends to cover the side of inner core (4), and covers at least the preceding limb (2) that adjoins with core (4) and the zone (6,7) of tail edge (3);
In preceding limb (2) and the tail edge (3) at least one has at least an end place at blade from the outstanding extension (10,11,12,13) of inner core (4), so that the attachment (14,15,16,17) that carrying is used for attached blade (1) and cooperates with the attachment of turbojet engine housing (20).
CN2011800425646A 2010-09-06 2011-09-05 Turbojet casing and turbojet receiving such casings Pending CN103080562A (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1057072 2010-09-06
FR1057072A FR2964427B1 (en) 2010-09-06 2010-09-06 CARTRIDGE OF TURBOJET AND TURBOJET RECEIVING SUCH CARTERS
PCT/EP2011/065339 WO2012032017A1 (en) 2010-09-06 2011-09-05 Turbojet casing and turbojet receiving such casings

Publications (1)

Publication Number Publication Date
CN103080562A true CN103080562A (en) 2013-05-01

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CN2011800425646A Pending CN103080562A (en) 2010-09-06 2011-09-05 Turbojet casing and turbojet receiving such casings

Country Status (8)

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US (1) US20130251519A1 (en)
EP (1) EP2614258A1 (en)
CN (1) CN103080562A (en)
BR (1) BR112013004717A2 (en)
CA (1) CA2810181A1 (en)
FR (1) FR2964427B1 (en)
RU (1) RU2544107C2 (en)
WO (1) WO2012032017A1 (en)

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US11795831B2 (en) * 2020-04-17 2023-10-24 Rtx Corporation Multi-material vane for a gas turbine engine
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Also Published As

Publication number Publication date
EP2614258A1 (en) 2013-07-17
BR112013004717A2 (en) 2016-05-17
FR2964427B1 (en) 2014-05-09
RU2013115370A (en) 2014-10-20
CA2810181A1 (en) 2012-03-15
FR2964427A1 (en) 2012-03-09
RU2544107C2 (en) 2015-03-10
US20130251519A1 (en) 2013-09-26
WO2012032017A1 (en) 2012-03-15

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