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RU2013115370A - TURBOJET ENGINE HOUSING AND TURBOREACTIVE ENGINE CONTAINING SUCH HOUSINGS - Google Patents

TURBOJET ENGINE HOUSING AND TURBOREACTIVE ENGINE CONTAINING SUCH HOUSINGS Download PDF

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Publication number
RU2013115370A
RU2013115370A RU2013115370/06A RU2013115370A RU2013115370A RU 2013115370 A RU2013115370 A RU 2013115370A RU 2013115370/06 A RU2013115370/06 A RU 2013115370/06A RU 2013115370 A RU2013115370 A RU 2013115370A RU 2013115370 A RU2013115370 A RU 2013115370A
Authority
RU
Russia
Prior art keywords
blades
casing
annular element
turbojet engine
housing
Prior art date
Application number
RU2013115370/06A
Other languages
Russian (ru)
Other versions
RU2544107C2 (en
Inventor
Патрик ДЁНЛАВИ
Ришар МАССОН
Бертран ДЕЖУАЙО
Original Assignee
Мессье-Бюгатти-Довти
Эрсэль
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 Мессье-Бюгатти-Довти, Эрсэль filed Critical Мессье-Бюгатти-Довти
Publication of RU2013115370A publication Critical patent/RU2013115370A/en
Application granted granted Critical
Publication of RU2544107C2 publication Critical patent/RU2544107C2/en

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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

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

1. Корпус турбореактивного двигателя, выполненный с возможностью установки в нем множества лопаток и содержащий средства (21, 30) крепления конца каждой лопатки на корпусе, отличающийся тем, что средства крепления расположены на стороне корпуса, противоположной лопаткам, при этом корпус содержит отверстия (26), через которые проходят концы лопаток для их взаимодействия со средствами крепления корпуса.2. Корпус по п.1, отличающийся тем, что средства крепления содержат кольцевой элемент (21, 30), проходящий вокруг корпуса.3. Корпус по п.2, отличающийся тем, что кольцевой элемент содержит, по меньшей мере, одну периферическую направляющую (21), в которую заходят концы (24) элементов (23) крепления концов лопаток.4. Корпус по п.2, отличающийся тем, что кольцевой элемент содержит периферический уголок (30), на котором непосредственно закреплены концы лопаток.5. Корпус по п.2, отличающийся тем, что он выполнен из длинных волокон, связанных термопластической смолой, при этом кольцевой элемент (21, 30) получен посредством пултрузии и пропитан термопластической смолой, свариваемой с термопластической смолой корпуса, при этом весь узел соединен посредством горячего прессования.6. Турбореактивный двигатель, содержащий, по меньшей мере, один корпус по одному из п.п.1-5 и множество лопаток, каждая из которых имеет конец, соединенный с корпусом.7. Турбореактивный двигатель по п.6, отличающийся тем, что каждая из лопаток содержит удлиненный моноблочный передний участок (2), вырезанный из пултрудированного профиля, содержащего связанные смолой волокна, и образующий переднюю кромку, удлиненный моноблочный задний участок (3), вырезанный из пултрудирован�1. A body of a turbojet engine made with the possibility of installing a plurality of blades in it and containing means (21, 30) for fastening the end of each blade to the body, characterized in that the means of attachment are located on the side of the body opposite to the blades, and the body contains holes (26 ), through which the ends of the blades pass for their interaction with the means of fastening the body. 2. The body according to claim 1, characterized in that the fastening means comprise an annular element (21, 30) extending around the body. The housing according to claim 2, characterized in that the annular element contains at least one peripheral guide (21), into which the ends (24) of the elements (23) for fastening the ends of the blades enter. The housing according to claim 2, characterized in that the annular element comprises a peripheral angle (30), on which the ends of the blades are directly fixed. The body according to claim 2, characterized in that it is made of long fibers bonded with a thermoplastic resin, wherein the annular element (21, 30) is obtained by pultrusion and impregnated with a thermoplastic resin welded with the thermoplastic resin of the body, while the whole assembly is connected by means of a hot pressing. 6. A turbojet engine comprising at least one housing according to one of claims 1 to 5 and a plurality of blades, each of which has an end connected to the housing. The turbojet engine according to claim 6, characterized in that each of the blades comprises an elongated monoblock front section (2) cut from a pultruded profile containing resin-bonded fibers and forming a leading edge, an elongated monoblock rear section (3) cut from pultruded�

Claims (7)

1. Корпус турбореактивного двигателя, выполненный с возможностью установки в нем множества лопаток и содержащий средства (21, 30) крепления конца каждой лопатки на корпусе, отличающийся тем, что средства крепления расположены на стороне корпуса, противоположной лопаткам, при этом корпус содержит отверстия (26), через которые проходят концы лопаток для их взаимодействия со средствами крепления корпуса.1. The casing of a turbojet engine, configured to install a plurality of vanes in it and comprising means (21, 30) for attaching the end of each vane to the casing, characterized in that the fastening means are located on the side of the casing opposite the blades, the casing comprising holes (26 ) through which the ends of the blades pass for their interaction with the means of fixing the casing. 2. Корпус по п.1, отличающийся тем, что средства крепления содержат кольцевой элемент (21, 30), проходящий вокруг корпуса.2. The housing according to claim 1, characterized in that the fastening means comprise an annular element (21, 30) extending around the housing. 3. Корпус по п.2, отличающийся тем, что кольцевой элемент содержит, по меньшей мере, одну периферическую направляющую (21), в которую заходят концы (24) элементов (23) крепления концов лопаток.3. The housing according to claim 2, characterized in that the annular element comprises at least one peripheral guide (21), into which the ends (24) of the blade ends attachment elements (23) enter. 4. Корпус по п.2, отличающийся тем, что кольцевой элемент содержит периферический уголок (30), на котором непосредственно закреплены концы лопаток.4. The housing according to claim 2, characterized in that the annular element contains a peripheral corner (30), on which the ends of the blades are directly fixed. 5. Корпус по п.2, отличающийся тем, что он выполнен из длинных волокон, связанных термопластической смолой, при этом кольцевой элемент (21, 30) получен посредством пултрузии и пропитан термопластической смолой, свариваемой с термопластической смолой корпуса, при этом весь узел соединен посредством горячего прессования.5. The housing according to claim 2, characterized in that it is made of long fibers bonded with a thermoplastic resin, while the annular element (21, 30) is obtained by pultrusion and impregnated with a thermoplastic resin welded to the thermoplastic resin of the housing, while the entire assembly is connected by hot pressing. 6. Турбореактивный двигатель, содержащий, по меньшей мере, один корпус по одному из п.п.1-5 и множество лопаток, каждая из которых имеет конец, соединенный с корпусом.6. A turbojet engine containing at least one casing according to one of claims 1 to 5 and a plurality of blades, each of which has an end connected to the casing. 7. Турбореактивный двигатель по п.6, отличающийся тем, что каждая из лопаток содержит удлиненный моноблочный передний участок (2), вырезанный из пултрудированного профиля, содержащего связанные смолой волокна, и образующий переднюю кромку, удлиненный моноблочный задний участок (3), вырезанный из пултрудированного профиля, содержащего связанные смолой волокна, и образующий заднюю кромку, центральный участок (4), образующий сердцевину, проходящую между передней кромкой (2) и задней кромкой (3), внешний слой (5), вырезанный из пропитанной смолой волокнистой ткани, расположенный так, чтобы перекрывать боковые стороны сердцевины (4), и перекрывающий, по меньшей мере, зоны (6, 7) передней кромки (2) и задней кромки (3), смежные с центральным участком (4), при этом, по меньшей мере, передняя кромка (2) или задняя кромка (3) имеет продолжения (10, 11, 12, 13), выступающие из сердцевины (4), по меньшей мере, с одной стороны лопатки (1) и выполненные с возможностью установки на них средств крепления (14, 15, 16, 17) лопатки (1), взаимодействующих со средствами (20) крепления корпуса турбореактивного двигателя. 7. A turbojet engine according to claim 6, characterized in that each of the blades contains an elongated monoblock front section (2) cut from a pultruded profile containing resin-bonded fibers and forming a leading edge, an elongated monoblock rear section (3) cut from a pultruded profile containing resin bound fibers and forming a trailing edge, a central portion (4) forming a core extending between the leading edge (2) and trailing edge (3), the outer layer (5) cut from the resin impregnated into a window fabric arranged so as to overlap the sides of the core (4), and overlapping at least the zones (6, 7) of the leading edge (2) and trailing edge (3) adjacent to the central portion (4), wherein at least the leading edge (2) or trailing edge (3) has extensions (10, 11, 12, 13) protruding from the core (4) of at least one side of the blade (1) and configured installing on them the fastening means (14, 15, 16, 17) of the blade (1) interacting with the means (20) for fastening the turbojet engine casing.
RU2013115370/06A 2010-09-06 2011-09-05 Housing of jet-turbine engine, and jet-turbine engine containing such housings RU2544107C2 (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 (2)

Publication Number Publication Date
RU2013115370A true RU2013115370A (en) 2014-10-20
RU2544107C2 RU2544107C2 (en) 2015-03-10

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Family Applications (1)

Application Number Title Priority Date Filing Date
RU2013115370/06A RU2544107C2 (en) 2010-09-06 2011-09-05 Housing of jet-turbine engine, and jet-turbine engine containing such housings

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)

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Also Published As

Publication number Publication date
EP2614258A1 (en) 2013-07-17
US20130251519A1 (en) 2013-09-26
BR112013004717A2 (en) 2016-05-17
FR2964427B1 (en) 2014-05-09
FR2964427A1 (en) 2012-03-09
RU2544107C2 (en) 2015-03-10
CA2810181A1 (en) 2012-03-15
CN103080562A (en) 2013-05-01
WO2012032017A1 (en) 2012-03-15

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Effective date: 20150906