WO2011131906A1 - Dispositif d'evaluation de fatigue thermomecanique d'un materiau - Google Patents
Dispositif d'evaluation de fatigue thermomecanique d'un materiau Download PDFInfo
- Publication number
- WO2011131906A1 WO2011131906A1 PCT/FR2011/050905 FR2011050905W WO2011131906A1 WO 2011131906 A1 WO2011131906 A1 WO 2011131906A1 FR 2011050905 W FR2011050905 W FR 2011050905W WO 2011131906 A1 WO2011131906 A1 WO 2011131906A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- channels
- fins
- support
- specimen
- hot wall
- Prior art date
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N25/00—Investigating or analyzing materials by the use of thermal means
- G01N25/72—Investigating presence of flaws
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/60—Investigating resistance of materials, e.g. refractory materials, to rapid heat changes
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/022—Environment of the test
- G01N2203/0222—Temperature
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/022—Environment of the test
- G01N2203/0222—Temperature
- G01N2203/0226—High temperature; Heating means
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/022—Environment of the test
- G01N2203/0236—Other environments
- G01N2203/0242—With circulation of a fluid
Definitions
- the invention relates to a thermomechanical fatigue evaluation device of a material subjected to a high thermal flux; it relates more particularly to a functional assembly making it possible to subject a sample of a given material to such a thermal flux, for example to assess the reliability of the prediction of the lifetime of a combustion chamber of a cryogenic rocket engine carried out at least partly from the material (alloy) considered.
- EDP elasto-visco-plastic type of life
- the desired flux range must be representative of that encountered in a regenerative rocket motor circuit, that is to say, to reach or exceed 100 MW / m 2 over a circular area with a diameter of at least 5 mm.
- the invention overcomes these disadvantages.
- the objective of the invention is therefore to "put in situation" the models, in a realistic industrial context.
- Validation is based on the ability of the developed technological test to be subjected locally to a large heat flux so as to reveal the same physical phenomena of degradation as those found, for example, on the channels of a real circuit Regenerative cryogenic rocket engine, namely:
- Another objective is to be able to impose such a high level of heat flow with relatively simple heating means while using an "industrial” cooling system that is to say using a non-cryogenic cooling fluid, this for to guarantee relatively low test costs.
- thermomechanical fatigue evaluation device for a material subjected to a heat flux, characterized in that it comprises:
- an intermediate part comprising parallel fins shaped and dimensioned to fit into said channels between said blades to define in the vicinity of said inner face of the hot wall a cooling fluid circulation passage composed of several parallel sections separated by said blades; , the section of said passage being defined by the engagement of said fins in said parallel channels,
- the heating means comprise a plasma torch directed towards said outer face of said hot wall; a low-pressure blown arc plasma torch is preferably used.
- said test piece is made in a block of said material, in which said parallel channels are made.
- said parallel channels are made. These are for example obtained by milling so that the hot wall is essentially constituted by the thickness of the material left between the bottom of the channels and the outer face of the block.
- said test piece comprises at least one temperature sensor housed in a blind hole made in a said blade, to a predetermined distance from said outer face of said hot wall.
- a sensor may be constituted by a thermocouple.
- the parallel channels of said test piece are longer than said fins of the insert and extend beyond the ends of these fins.
- the duct elements of said support open on either side of said insert, respectively, facing said sample channels, between the ends of these channels and the ends of said fins.
- the ends of the fins are rounded to a curvature corresponding to the shape of the ends of the channels of said specimen (the rounded ends of the channels resulting from their obtaining by milling) to define, opposite each orifice of a conduit element said support, a plenum chamber and guiding said cooling fluid.
- the cooling fluid flows in the aforementioned cooling fluid circulation passage in a regular manner, without turbulence.
- the insert is for example interposed between the support and the test piece.
- said support comprises, on one side, a counterbore of insertion of said intermediate part. More specifically, a base thereof, carrying said fins, is embedded in this countersink and the test piece is fixed to the support by sandwiching said intermediate part between them.
- FIG. 1 is a general schematic perspective exploded view of a part of the device.
- FIG. 4 is a section IV-IV of FIG. 5;
- FIG. 5 is a V-V section of FIG. 4;
- FIG. 6 is a view on a larger scale of the box VI of FIG. 5;
- FIG. 7 is a schematic view of the entire device shown in operation.
- the device according to the invention comprises a chamber 11 in which it can be evacuated and which contains a plasma torch 13 carried by a robot arm 15, controlled and, opposite it a subset test 20 constituted by the assembly of a specimen 21, a support 22 and an intermediate piece 23, comb-shaped profile, which will be described later.
- This subassembly is installed at the end of a mast 25 so that an outer face of a wall, said hot wall 27 of the test piece 21 is exposed to the heat flux delivered by the plasma torch 13.
- fixing the support piece 22 on the mast 25 is advantageously used for this purpose two screws 37 located on an edge between the two cooling fluid supply ports 35.
- the robot is programmed so that said torch can move opposite said hot wall, perpendicular thereto.
- Several regions of the hot rectangular wall of the specimen can thus be subjected to the action of the plasma torch.
- the test piece 21 is made of the material to be tested.
- the hot wall 27 is relatively thin and its inner face 31 is extended by parallel blades 29. These are attached to said inner face and form between them parallel channels 33.
- the test piece is made in a block of said material in the form of a rectangular parallelepiped (for example in an alloy based on copper) in which are formed the parallel channels 33, preferably by milling. As a result, ends of the parallel channels are rounded as shown.
- the support 22 which receives said specimen 21 is in the form of a rectangular parallelepiped-shaped machined block and has at its ends duct elements 35 which open on the face 36 on which the specimen 21 is fixed, by A set of screws 37.
- These internally threaded conduit members 35 allow the fitting of connectors 40 protruding from the face of the support opposite to the mounting face of the specimen. As shown in Figure 6, these two connections are connected to pipes 41 through sealingly the wall of the enclosure 11 in which is evacuated.
- the ducts are connected to an outdoor unit 43 comprising a coolant reservoir and a booster group consisting for example of at least one pump.
- the cooling circuit may be a closed circuit that may also include a fluid refrigeration system for maintaining the temperature of said fluid at the inlet 35 of the specimen, regulated within a determined temperature range.
- the cooling fluid may for example be refrigerated distilled water and circulated under a working pressure of several tens of bar.
- the intermediate piece 23 with a comb-shaped profile (in a right cross section perpendicular to its longitudinal direction, see FIG. 6) has parallel fins 45 shaped and dimensioned to fit into said channels 33 between the blades 29.
- L The thickness of the fins corresponds substantially to the width of the channels of the specimen 21.
- the height of the fins is determined to define, in the vicinity of said inner face 31 of the hot wall, a cooling fluid circulation passage 47 of predetermined section. , which is composed of several parallel sections separated by said blades 29.
- the flow section of said passage along said hot wall is defined by the engagement of said fins 45 in said parallel channels 33, it being understood that the fins have a height of lower commitment to the depth of the channels.
- the fins of the intermediate part are machined according to the desired section of the coolant circulation passage so that the blades of the specimen come closest to the throat bottoms. said intermediate piece formed between said fins and with a small but not zero clearance.
- the width of said hot wall is limited in the mass of the test piece by the parallel channels 33 which are milled therein.
- the milling depth of the channels determines the thickness of the hot wall between the bottoms of the parallel channels and the outer face 28 of the test piece.
- the edges of the hot wall longitudinally, are thicker; the extra thickness is about 50%.
- the two parallel lateral channels 33 of the specimen are shallower than the middle channels, here five in number, which effectively increases the thickness of the hot wall 27 along the edges. As shown in FIG.
- the overall natural deformation of the hot wall during the tests generally consists of a bulge under the combined effect of the differential thermal expansion between the heated outer surface and the surface. cooled interior. This bulge is further promoted by the effect of the internal pressure of the coolant.
- the extra thickness of the hot wall 27 along its longitudinal edges avoids a break.
- the blades of the specimen can advantageously be glued with epoxy resin with the bottoms of the grooves of the intermediate part.
- the parallel channels 33 of the specimen are longer than the fins 45 of the intermediate part 23 and extend beyond the ends of said fins. Consequently, the duct elements 35 of the support open on either side of said intermediate part 23, respectively, facing the channels 33 of the test piece. Each duct member 35 opens out between the ends of said channels 33 and the ends of said fins 45.
- the ends of the vanes are rounded corresponding to the shape of the ends of the specimen channels (these resulting rounded ends milling said channels).
- a plenum and guiding chamber 50 of the cooling fluid which allows a non-turbulent flow of said fluid, through the fluid circulation passage 47, defined in the vicinity of the inner face 31 of the hot wall.
- the intermediate piece 23 is clamped between the support 22 and the test piece 21 when the latter is fixed by the screws 37 to said support. More particularly, the latter comprises, on a mounting face of the test piece, an insert counterbore 53 of said intermediate part 23. A base 55 of this intermediate part, which carries the fins 45, is embedded in this counterbore . Said intermediate piece is thus immobilized between the bottom of said countersink and the fields of said blades 29 of the specimen. As indicated above, the assembly can be improved by depositing an epoxy resin 57 on the fields of the blades, at the time of assembly so as to limit the appearance of bulging of the heated wall 27.
- the support 22 and the test piece 21 are fixed to each other with the interposition of a seal 60 surrounding both the orifices of said duct elements 35 and said countersink 53 receiving the base 55 of the insert.
- This seal is housed in a closed contour groove 61 excavated on the face of the support which receives the test piece.
- said test piece comprises at least one temperature sensor 63, for example of the thermocouple type.
- thermocouple for example of the thermocouple type.
- four pairs of temperature sensors 63 spaced longitudinally are provided.
- Each pair of temperature sensors makes it possible to define on the same test piece a test zone for which it is possible to know the temperature evolution during the test. .
- Each zone is therefore equipped with two thermocouples 63 for reasons of measurement redundancy. More particularly, as shown, such a sensor (thermocouple) is housed in a blind hole 65 formed in a blade 29 of the test piece to a predetermined distance from said outer face 28 of the hot wall.
- the intermediate part 23 comprises, for each sensor, a through hole 66 formed through the base 55 and opening between two fins 45 thereof, opposite a corresponding blind hole 65.
- the support comprises meanwhile, for each pair of sensors, a through hole 67 of larger diameter, allowing communication with the two adjacent holes 66 of the insert.
- threaded plugs 69 are engaged in threads of these holes. They comprise holes permitting the passage of electrical wires 70.
- the position of the sensors is fixed by injecting epoxy resin into the holes that house them.
- the electrical wires are connected to a measurement unit 71.
- the different zones defined in the hot wall 27 around the locations of the pairs of sensors may be advantageous for the different zones defined in the hot wall 27 around the locations of the pairs of sensors, to place the latter at different depths under the outer face of the hot wall, for example at 0.5, 1, 2 and 3 mm under this outer face 28 of the hot wall 27, to be able to know the temperature at different depths of the hot wall. It suffices for this to adjust accordingly the depth of the blind holes 65 of the same pair of sensors.
- the doubling of the measurement channels advantageously makes the measurement of temperature reliable.
- the speed of approach of the torch, the minimum distance to the hot wall, the exposure time to the heat flow constitute the parameters of adjustment of the test to implement multiple forms of thermal stresses representative of different aspects of the operation of a rocket engine (rapid thermal transient, slow, stabilized, change of heat flow level, etc.).
- the spacer part 23 makes it possible to keep the parallel blades of the test piece preventing them from bending and rotating when the hot wall deforms.
- the spacing of the blades 29 is guaranteed, which avoids a closing effect or section variation of said cooling fluid circulation passage defined between the blades 23 and the fins of the insert.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Immunology (AREA)
- Biochemistry (AREA)
- Pathology (AREA)
- Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Analytical Chemistry (AREA)
- General Physics & Mathematics (AREA)
- General Health & Medical Sciences (AREA)
- Mechanical Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
- Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)
- Investigating Or Analyzing Materials Using Thermal Means (AREA)
- Investigating, Analyzing Materials By Fluorescence Or Luminescence (AREA)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/642,022 US8979360B2 (en) | 2010-04-23 | 2011-04-20 | Device evaluating thermomechanical fatigue of a material |
JP2013505524A JP5819402B2 (ja) | 2010-04-23 | 2011-04-20 | 材料のサーモメカニカル疲労の評価装置 |
RU2012147346/28A RU2561011C2 (ru) | 2010-04-23 | 2011-04-20 | Устройство для оценки термомеханической усталости материала |
DE112011101414.7T DE112011101414B4 (de) | 2010-04-23 | 2011-04-20 | Vorrichtung zur Bewertung der thermomechanischen Ermüdung eines Materials |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1053118A FR2959313B1 (fr) | 2010-04-23 | 2010-04-23 | Dispositif d'evaluation de fatigue thermomecanique d'un materiau |
FR1053118 | 2010-04-23 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2011131906A1 true WO2011131906A1 (fr) | 2011-10-27 |
Family
ID=43828006
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2011/050905 WO2011131906A1 (fr) | 2010-04-23 | 2011-04-20 | Dispositif d'evaluation de fatigue thermomecanique d'un materiau |
Country Status (6)
Country | Link |
---|---|
US (1) | US8979360B2 (fr) |
JP (1) | JP5819402B2 (fr) |
DE (1) | DE112011101414B4 (fr) |
FR (1) | FR2959313B1 (fr) |
RU (1) | RU2561011C2 (fr) |
WO (1) | WO2011131906A1 (fr) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2570103C1 (ru) * | 2014-08-26 | 2015-12-10 | Российская Федерация, от имени которой выступает Государственная корпорация по атомной энергии "Росатом" | Установка для термомеханических испытаний |
RU2624613C1 (ru) * | 2016-02-25 | 2017-07-04 | Общество с ограниченной ответственностью "Всесоюзный научно-исследовательский центр транспортных технологий" (ООО "ВНИЦТТ") | Способ испытаний металлов на растяжение-сжатие и образец для его осуществления |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2987126B1 (fr) * | 2012-02-16 | 2014-03-28 | Peugeot Citroen Automobiles Sa | Procede d'evaluation de la resistance a la fatigue thermomecanique d'au moins un materiau |
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US3029635A (en) * | 1956-07-09 | 1962-04-17 | Amalgamated Growth Ind Inc | High-temperature testing apparatus |
US3709026A (en) * | 1968-11-12 | 1973-01-09 | Kms Ind Inc | Apparatus and method for simulating spacecraft erosion |
FR2674333A1 (fr) * | 1991-03-22 | 1992-09-25 | Isover Formtec Sa | Dispositif pour tester la resistance d'un materiau a un jet gazeux. |
EP0588739A1 (fr) * | 1992-09-14 | 1994-03-23 | AEROSPATIALE Société Nationale Industrielle | Procédé d'essai thermomécanique par simulation d'un bouclier thermique ou analogue et dispositif pour sa mise en oeuvre |
GB2332747A (en) * | 1997-12-22 | 1999-06-30 | Ford Global Tech Inc | Accelerated thermal fatigue testing of engine combustion chambers |
DE102006009465A1 (de) * | 2006-03-01 | 2007-09-06 | Siemens Ag | Verfahren zum Testen der Beständigkeit eines Schichtsystems, insbesondere eines Wärmedämmschicht-Systems, und Testvorrichtung |
EP1936354A1 (fr) * | 2006-12-21 | 2008-06-25 | Snecma Propulsion Solide | Dispositif et procédé d'essai thermo-érosif pour des matériaux de protections thermiques de propulseurs à propergol solide |
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JPS60177252A (ja) * | 1984-02-24 | 1985-09-11 | Toyota Motor Corp | セラミツク部品の強度検査方法 |
SU1495696A1 (ru) * | 1986-11-11 | 1989-07-23 | Ленинградский технологический институт холодильной промышленности | Способ неразрушающего определени теплофизических свойств материалов теплозащитных покрытий на металлическом основании |
US7133726B1 (en) * | 1997-03-28 | 2006-11-07 | Applera Corporation | Thermal cycler for PCR |
US7035104B2 (en) * | 2002-08-06 | 2006-04-25 | Mudawar Thermal Systems Inc. | Apparatus for heat transfer and critical heat flux enhancement |
DE10240590A1 (de) * | 2002-08-28 | 2004-03-11 | E.G.O. Elektro-Gerätebau GmbH | Vorrichtung zur Erfassung der Temperatur eines Mediums, das durch einen Kanal strömt |
JP2004125575A (ja) * | 2002-10-02 | 2004-04-22 | Ishikawajima Harima Heavy Ind Co Ltd | 熱サイクル試験方法および熱サイクル試験用治具 |
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US7869184B2 (en) * | 2005-11-30 | 2011-01-11 | Lam Research Corporation | Method of determining a target mesa configuration of an electrostatic chuck |
JP4930713B2 (ja) * | 2007-06-12 | 2012-05-16 | 株式会社Ihi | 熱サイクル試験装置及び熱サイクル試験方法 |
FR2962537B1 (fr) * | 2010-07-06 | 2012-08-31 | Univ Maine | Dispositif pour la mesure d'un flux thermique |
CN103875071B (zh) * | 2011-09-27 | 2015-08-05 | 丰田自动车株式会社 | 冷却装置的异常检测装置和异常检测方法 |
EP2769190A4 (fr) * | 2011-10-20 | 2015-07-08 | Cambria Ltd | Dispositif de mesure de résistance thermique |
-
2010
- 2010-04-23 FR FR1053118A patent/FR2959313B1/fr active Active
-
2011
- 2011-04-20 WO PCT/FR2011/050905 patent/WO2011131906A1/fr active Application Filing
- 2011-04-20 JP JP2013505524A patent/JP5819402B2/ja active Active
- 2011-04-20 DE DE112011101414.7T patent/DE112011101414B4/de active Active
- 2011-04-20 US US13/642,022 patent/US8979360B2/en active Active
- 2011-04-20 RU RU2012147346/28A patent/RU2561011C2/ru active
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US3029635A (en) * | 1956-07-09 | 1962-04-17 | Amalgamated Growth Ind Inc | High-temperature testing apparatus |
US3709026A (en) * | 1968-11-12 | 1973-01-09 | Kms Ind Inc | Apparatus and method for simulating spacecraft erosion |
FR2674333A1 (fr) * | 1991-03-22 | 1992-09-25 | Isover Formtec Sa | Dispositif pour tester la resistance d'un materiau a un jet gazeux. |
EP0588739A1 (fr) * | 1992-09-14 | 1994-03-23 | AEROSPATIALE Société Nationale Industrielle | Procédé d'essai thermomécanique par simulation d'un bouclier thermique ou analogue et dispositif pour sa mise en oeuvre |
GB2332747A (en) * | 1997-12-22 | 1999-06-30 | Ford Global Tech Inc | Accelerated thermal fatigue testing of engine combustion chambers |
DE102006009465A1 (de) * | 2006-03-01 | 2007-09-06 | Siemens Ag | Verfahren zum Testen der Beständigkeit eines Schichtsystems, insbesondere eines Wärmedämmschicht-Systems, und Testvorrichtung |
EP1936354A1 (fr) * | 2006-12-21 | 2008-06-25 | Snecma Propulsion Solide | Dispositif et procédé d'essai thermo-érosif pour des matériaux de protections thermiques de propulseurs à propergol solide |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2570103C1 (ru) * | 2014-08-26 | 2015-12-10 | Российская Федерация, от имени которой выступает Государственная корпорация по атомной энергии "Росатом" | Установка для термомеханических испытаний |
RU2624613C1 (ru) * | 2016-02-25 | 2017-07-04 | Общество с ограниченной ответственностью "Всесоюзный научно-исследовательский центр транспортных технологий" (ООО "ВНИЦТТ") | Способ испытаний металлов на растяжение-сжатие и образец для его осуществления |
Also Published As
Publication number | Publication date |
---|---|
FR2959313A1 (fr) | 2011-10-28 |
RU2012147346A (ru) | 2014-05-27 |
JP2013525779A (ja) | 2013-06-20 |
DE112011101414T5 (de) | 2013-02-28 |
FR2959313B1 (fr) | 2012-05-11 |
JP5819402B2 (ja) | 2015-11-24 |
RU2561011C2 (ru) | 2015-08-20 |
DE112011101414B4 (de) | 2023-06-15 |
US20130121368A1 (en) | 2013-05-16 |
US8979360B2 (en) | 2015-03-17 |
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