CN103080562A - Turbojet casing and turbojet receiving such casings - Google Patents
Turbojet casing and turbojet receiving such casings Download PDFInfo
- 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
Links
Images
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
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- 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
Landscapes
- 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
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.
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.
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.
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).
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 |
Family
ID=43770444
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN2011800425646A Pending CN103080562A (en) | 2010-09-06 | 2011-09-05 | Turbojet casing and turbojet receiving such casings |
Country Status (8)
Country | Link |
---|---|
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) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN109372798A (en) * | 2018-12-13 | 2019-02-22 | 中国航发沈阳发动机研究所 | A kind of fan blade |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3077328B1 (en) * | 2018-01-30 | 2020-07-31 | Safran Aircraft Engines | TURBOREACTOR INCLUDING A PART FOR CONNECTING A FIN WITH AN ELASTIC BODY AND PROCESS FOR ASSEMBLING A FIN |
US11572796B2 (en) | 2020-04-17 | 2023-02-07 | Raytheon Technologies Corporation | Multi-material vane for a gas turbine engine |
US11795831B2 (en) * | 2020-04-17 | 2023-10-24 | Rtx Corporation | Multi-material vane for a gas turbine engine |
US11879360B2 (en) * | 2020-10-30 | 2024-01-23 | General Electric Company | Fabricated CMC nozzle assemblies for gas turbine engines |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
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GB732919A (en) * | 1953-07-15 | 1955-06-29 | Rolls Royce | Improvements in or relating to blade assemblies of turbo-machines such as compressors and turbines |
GB748912A (en) * | 1950-08-01 | 1956-05-16 | Rolls Royce | Improvements in or relating to blade assemblies of compressors and turbines and likemachines |
CN101749181A (en) * | 2008-12-12 | 2010-06-23 | 通用电气公司 | Turbine blade and method of fabricating the same |
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US748912A (en) * | 1904-01-05 | Type-writing machine | ||
GB599391A (en) * | 1945-05-25 | 1948-03-11 | Power Jets Res & Dev Ltd | Improvements in and relating to axial flow compressors, turbines and the like machines |
US267405A (en) * | 1882-11-14 | debes | ||
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GB267405A (en) * | 1926-09-09 | 1927-03-17 | Charles Oliver | Improvements in or relating to shrouding for turbine blades and the like |
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US4395195A (en) * | 1980-05-16 | 1983-07-26 | United Technologies Corporation | Shroud ring for use in a gas turbine engine |
US4648921A (en) * | 1980-10-02 | 1987-03-10 | United Technologies Corporation | Method of making fiber reinforced articles |
US4470862A (en) * | 1982-05-27 | 1984-09-11 | United Technologies Corporation | Manufacture of fiber reinforced articles |
US4710097A (en) * | 1986-05-27 | 1987-12-01 | Avco Corporation | Stator assembly for gas turbine engine |
FR2697285B1 (en) * | 1992-10-28 | 1994-11-25 | Snecma | Blade end locking system. |
FR2699498B1 (en) * | 1992-12-23 | 1995-03-10 | Eurocopter France | Blade made of thermoplastic composite, in particular for a faired tail rotor of a helicopter, and its manufacturing process. |
US5494404A (en) * | 1993-12-22 | 1996-02-27 | Alliedsignal Inc. | Insertable stator vane assembly |
TWI233444B (en) * | 1998-10-30 | 2005-06-01 | Toray Industries | Thermoplastic resin composition, production thereof, and molded article thereof |
US6409472B1 (en) * | 1999-08-09 | 2002-06-25 | United Technologies Corporation | Stator assembly for a rotary machine and clip member for a stator assembly |
DE60026687T2 (en) * | 2000-12-06 | 2006-11-09 | Techspace Aero S.A. | Stator stage of a compressor |
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2010
- 2010-09-06 FR FR1057072A patent/FR2964427B1/en not_active Expired - Fee Related
-
2011
- 2011-09-05 CN CN2011800425646A patent/CN103080562A/en active Pending
- 2011-09-05 BR BR112013004717A patent/BR112013004717A2/en not_active IP Right Cessation
- 2011-09-05 CA CA2810181A patent/CA2810181A1/en not_active Abandoned
- 2011-09-05 WO PCT/EP2011/065339 patent/WO2012032017A1/en active Application Filing
- 2011-09-05 RU RU2013115370/06A patent/RU2544107C2/en not_active IP Right Cessation
- 2011-09-05 EP EP11754367.8A patent/EP2614258A1/en not_active Withdrawn
- 2011-09-05 US US13/820,545 patent/US20130251519A1/en not_active Abandoned
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GB748912A (en) * | 1950-08-01 | 1956-05-16 | Rolls Royce | Improvements in or relating to blade assemblies of compressors and turbines and likemachines |
US2772856A (en) * | 1950-08-01 | 1956-12-04 | Rolls Royce | Structural elements for turbo-machines such as compressors or turbines of gasturbineengines |
GB732919A (en) * | 1953-07-15 | 1955-06-29 | Rolls Royce | Improvements in or relating to blade assemblies of turbo-machines such as compressors and turbines |
CN101749181A (en) * | 2008-12-12 | 2010-06-23 | 通用电气公司 | Turbine blade and method of fabricating the same |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN109372798A (en) * | 2018-12-13 | 2019-02-22 | 中国航发沈阳发动机研究所 | A kind of fan blade |
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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Legal Events
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C06 | Publication | ||
PB01 | Publication | ||
C10 | Entry into substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
AD01 | Patent right deemed abandoned |
Effective date of abandoning: 20160914 |
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C20 | Patent right or utility model deemed to be abandoned or is abandoned |