EP0401106A1 - Reaktionskammer und Verfahren zu ihrer Herstellung - Google Patents

Reaktionskammer und Verfahren zu ihrer Herstellung Download PDF

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Publication number
EP0401106A1
EP0401106A1 EP90401424A EP90401424A EP0401106A1 EP 0401106 A1 EP0401106 A1 EP 0401106A1 EP 90401424 A EP90401424 A EP 90401424A EP 90401424 A EP90401424 A EP 90401424A EP 0401106 A1 EP0401106 A1 EP 0401106A1
Authority
EP
European Patent Office
Prior art keywords
wall
chamber
densification
fluid
injection
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
EP90401424A
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English (en)
French (fr)
Other versions
EP0401106B1 (de
Inventor
Philippe H. Ramette
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.)
Societe Europeenne de Propulsion SEP SA
Original Assignee
Societe Europeenne de Propulsion SEP 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 Societe Europeenne de Propulsion SEP SA filed Critical Societe Europeenne de Propulsion SEP SA
Publication of EP0401106A1 publication Critical patent/EP0401106A1/de
Application granted granted Critical
Publication of EP0401106B1 publication Critical patent/EP0401106B1/de
Anticipated expiration legal-status Critical
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components

Definitions

  • the present invention relates to a reactor chamber, in particular a ramjet or turbojet, and more particularly a chamber of the type in which a fluid is introduced by transpiration through a porous refractory wall.
  • porous refractory material in a turboprop reaction tube is described in document GB-A-2 089 434.
  • the tube is formed by an internal conduit made of porous refractory material of low density and an external reinforcement whose presence is necessary due to the lack of mechanical strength of the porous refractory material.
  • the latter is formed from silica and alumina fibers, while the external reinforcement comprises a network of circumferential and axial tubes and an external metal or resin casing reinforced with carbon fibers.
  • the pipes can be traversed by a refrigerant or fuel and have perforated walls allowing the refrigerant or fuel to infiltrate the interior insulating material.
  • the object of the present invention is to provide a reactor chamber in which the functions of resistance to high temperatures, mechanical resistance and fuel injection can be ensured with a structure as simple as possible.
  • the wall of the reactor chamber is made of refractory composite material, comprising a reinforcement texture densified by a matrix, and comprises at least one injection zone defined by a porous wall part permeable to a fluid. to be injected into the chamber, the permeability of the or each part of the wall defining an injection zone resulting from less densification of the composite material in comparison with the rest of the wall which is impermeable to the fluid to be injected.
  • refractory composite material is meant here a ceramic or carbon matrix composite.
  • the or each part of the wall defining an injection zone is for example in the form of a ring whose surface opposite to that which constitutes an internal surface part of the chamber is in communication with a source of the fluid to be injected.
  • a ceramic matrix (CMC) or carbon matrix refractory composite material is particularly suitable for producing a reactor chamber in the wall of which one or more zones for injecting fluid by transpiration through a porous material are integrated.
  • thermostructural properties that is to say mechanical behavior and resistance to high temperatures, which make it suitable for producing structural elements of the chamber.
  • an external reinforcement around the composite wall such as that described in document GB-A-2 089 434, is not necessary.
  • the porosity of a composite can be easily controlled by acting on the volume ratio of fibers constituting its fibrous reinforcing texture and / or on the degree of densification by the material constituting the matrix, in order to obtain the permeability or the non-permeability to the fluid to be injected.
  • a material of type C / SiC carbon fiber reinforcement and matrix of silicon carbide) or of SiC / SiC type (fiber reinforcement essentially of silicon carbide and matrix of silicon carbide), or of type C / C protected (carbon fiber reinforcement, carbon matrix and anti-oxidation protection), may be suitable.
  • connection between the or each wall part defining an injection zone and the or each wall part forming the rest of the chamber is advantageously carried out by assembling all the constituent parts of the wall in an incompletely densified state relative to the level desired final densification for each of the parts, and by co-densification of the assembled wall parts.
  • This co-densification is preferably carried out by chemical vapor infiltration.
  • the chamber 10 is of cylindrical shape with circular section and comprises, in the direction of air flow (arrow A), an upstream sealed section 12, an injection ring 20 for injection of a gaseous fuel flow, and a downstream sealed section 14.
  • the interior surfaces of the sections 12, 14 and of the injection ring 20 define the cylindrical continuous internal wall of the ramjet chamber.
  • the outer surface of the ring 20 delimits a fuel injection chamber 22 which communicates with a fuel source (not shown).
  • the fuel is for example hydrogen which is injected in the gaseous state, the pressure prevailing in the injection chamber 22 being greater than that prevailing in the combustion chamber of the ramjet.
  • the ring 20 is made in a single piece of porous composite material with a ceramic or carbon matrix.
  • the porosity of the material constituting the ring 20 gives the latter the permeability necessary to allow the injection of the gas flow of fuel by transpiration through the injection ring.
  • the fuel flow injected into the combustion chamber is defined by the porosity of the injection ring, the length of the latter, and the pressure difference between the outer and inner surfaces of the ring.
  • the constituent material of the ring 20 is a composite material consisting of a fibrous reinforcement partially densified by a ceramic material or by carbon.
  • an annular preform is formed which constitutes the fibrous reinforcement.
  • the preform is made of carbon fibers or ceramic fibers, for example fibers essentially of silicon carbide.
  • the fiber preform is produced by winding on a mandrel of a strip of fabric until the desired thickness is obtained.
  • the superimposed layers of fabric can be linked together by needling or implantation of threads.
  • the preform is densified by gas or by liquid.
  • densification is carried out by chemical vapor infiltration of the material constituting the matrix, for example silicon carbide or carbon.
  • the preform is impregnated with a precursor of the material constituting the matrix, the latter then being obtained by heat treatment.
  • an injection ring made of ceramic material C / SiC can be produced by manufacturing a carbon fiber preform having a fiber volume ratio of approximately 35% and densifying it by chemical vapor infiltration of silicon carbide until reaching a residual porosity of about 40%.
  • the sections 12, 14 of the ramjet chamber are preferably also made of a composite material with a ceramic or carbon matrix.
  • a material having a reinforcement and a matrix of the same type as that of the injection ring 20 will be chosen.
  • the sections 12, 14 are sealed, the sealing being obtained by a densification sufficiently advanced to fill the porosity of the fibrous reinforcement until the material is impermeable.
  • connection between the sections 12, 14 of the wall of the chamber 10 and the injection ring 20 is produced by co-densification.
  • the sections 12, 14 and the ring 20 are produced separately while being incompletely densified with respect to the desired degree of final densification.
  • the elements are then assembled end to end and placed in an infiltration oven to undergo a final co-densification by chemical vapor infiltration.
  • the continuity of the matrix material at the interfaces between the sections 12, 14 and the ring 20 ensures the connection between these elements.
  • This final co-densification is continued until the desired degree of porosity is obtained for the injection ring 20, the sections 12, 14 having been previously sufficiently densified to finally obtain the desired seal.
  • the number of injection zones can be greater than 1 by providing one or more additional injection rings to carry out an additional injection of fuel or to carry out an injection of oxidant, for example for dilution purposes, downstream of the fuel injection.
  • shapes other than annular may be given to the injection areas.
  • the wall parts defining the injection zones can be produced and assembled with the rest of the wall of the chamber as described above with respect to the injection ring 20.
  • the injection of a gaseous combustible fluid inside a ramjet chamber can also be used in the case of the injection of a liquid fuel, by adapting for this purpose the porosity of the CMC or of the protected C / C in the injection zone.
  • the scope of the invention is not limited to ramjet chambers, whether they are subsonic or supersonic combustion, and also includes the chambers of turbojets.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Ceramic Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Products (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Moulding By Coating Moulds (AREA)
EP19900401424 1989-05-29 1990-05-29 Reaktionskammer und Verfahren zu ihrer Herstellung Expired - Lifetime EP0401106B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8907020 1989-05-29
FR8907020A FR2647534B1 (fr) 1989-05-29 1989-05-29 Chambre de reacteur et procede pour sa fabrication

Publications (2)

Publication Number Publication Date
EP0401106A1 true EP0401106A1 (de) 1990-12-05
EP0401106B1 EP0401106B1 (de) 1994-09-14

Family

ID=9382107

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19900401424 Expired - Lifetime EP0401106B1 (de) 1989-05-29 1990-05-29 Reaktionskammer und Verfahren zu ihrer Herstellung

Country Status (4)

Country Link
EP (1) EP0401106B1 (de)
JP (1) JPH0395308A (de)
DE (1) DE69012427T2 (de)
FR (1) FR2647534B1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999046540A1 (de) * 1998-03-10 1999-09-16 Siemens Aktiengesellschaft Brennkammer und verfahren zum betrieb einer brennkammer
RU2542652C1 (ru) * 2013-09-18 2015-02-20 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Гиперзвуковой прямоточный воздушно-реактивный двигатель
FR3070626A1 (fr) * 2017-09-07 2019-03-08 Safran Ceramics Procede de fabrication d'une piece en materiau composite munie d'un capteur

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
TW522127B (en) * 2001-02-21 2003-03-01 Daifuku Kk Cargo storage facility
RU2453719C1 (ru) * 2010-11-09 2012-06-20 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Способ организации горения в гиперзвуковом прямоточном воздушно-реактивном двигателе и гиперзвуковой прямоточный воздушно-реактивный двигатель

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2658332A (en) * 1951-03-21 1953-11-10 Carborundum Co Fluid cooled, refractory, ceramic lined rocket structure
US3114961A (en) * 1959-03-20 1963-12-24 Power Jets Res & Dev Ltd Treatment of porous bodies
DE1278319B (de) * 1963-11-28 1969-04-17 Bbc Brown Boveri & Cie Verfahren zum Schuetzen von durch heisse Medien ueberstrichenen Oberflaechenteilen eines hitzebestaendigen Koerpers
GB2053873A (en) * 1979-07-19 1981-02-11 Europ Propulsion High temperature thermal insulation material and method for making same
GB2089434A (en) * 1980-12-09 1982-06-23 Rolls Royce Composite Ducts for Jet Pipes

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2658332A (en) * 1951-03-21 1953-11-10 Carborundum Co Fluid cooled, refractory, ceramic lined rocket structure
US3114961A (en) * 1959-03-20 1963-12-24 Power Jets Res & Dev Ltd Treatment of porous bodies
DE1278319B (de) * 1963-11-28 1969-04-17 Bbc Brown Boveri & Cie Verfahren zum Schuetzen von durch heisse Medien ueberstrichenen Oberflaechenteilen eines hitzebestaendigen Koerpers
GB2053873A (en) * 1979-07-19 1981-02-11 Europ Propulsion High temperature thermal insulation material and method for making same
GB2089434A (en) * 1980-12-09 1982-06-23 Rolls Royce Composite Ducts for Jet Pipes

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999046540A1 (de) * 1998-03-10 1999-09-16 Siemens Aktiengesellschaft Brennkammer und verfahren zum betrieb einer brennkammer
RU2542652C1 (ru) * 2013-09-18 2015-02-20 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Гиперзвуковой прямоточный воздушно-реактивный двигатель
FR3070626A1 (fr) * 2017-09-07 2019-03-08 Safran Ceramics Procede de fabrication d'une piece en materiau composite munie d'un capteur
WO2019048791A1 (fr) * 2017-09-07 2019-03-14 Safran Ceramics Procede de fabrication d'une piece en materiau composite munie d'un capteur

Also Published As

Publication number Publication date
EP0401106B1 (de) 1994-09-14
FR2647534A1 (fr) 1990-11-30
DE69012427T2 (de) 1995-02-02
JPH0395308A (ja) 1991-04-19
FR2647534B1 (fr) 1991-09-13
DE69012427D1 (de) 1994-10-20

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