TURBOMACHINE MODULE COMPRISING A COMBUSTION CHAMBER AND A DEVICE FOR MEASURING COMBUSTION CHAMBER PARAMETERS AND CORRESPONDING TURBOMACHINE

Abstract

The invention relates to a turbomachine module comprising an annular combustion chamber having at least one wall (12) defining at least part of an enclosure and at least one measuring device (30) mounted on the wall (12). According to the invention, the measuring device (30) comprises a temperature probe (31) mounted on a radially external surface (32) of the wall (12) and an aerodynamically shaped housing (33) that at least partially surrounds the temperature probe (31), the housing (33) being mounted on the wall (12). Figure for the abstract: Fig. 4

Description

Title of the invention: TURBOMACHINE MODULE COMPRISING A COMBUSTION CHAMBER AND A COMBUSTION CHAMBER PARAMETER MEASUREMENT DEVICE AND CORRESPONDING TURBOMACHINE Technical field of the invention

[0001] The present invention relates to the aeronautical field. In particular, it aims at means for measuring certain parameters of an aircraft turbomachine. Technological background

[0002] Turbomachinery, and in particular aircraft turbomachinery, undergoes a multitude of tests and trials to verify and validate, firstly, their proper functioning and, secondly, their ability to maintain their integrity and performance. Validation of these tests and trials leads to certification authorizing their entry into service. In particular, these tests and trials involve measurements of certain aerodynamic flow parameters, such as pressure, temperature, and / or acceleration, using a measuring device.

[0003] There are areas in the turbomachine where installing measuring devices is difficult and where measurements are typically performed on test machines. This is the case for the combustion chamber, which includes a radially external wall subjected to significant mechanical stresses resulting from substantial thermal, pressure, and vibrational loads. This leads to significant expansion and differential displacement between this wall and an annular casing surrounding the chamber.

[0004] Document FR3023584 describes a measuring probe that is fixed to the radially external wall of the combustion chamber so as to measure its temperature. The measuring probe is fixed to the radially external wall by means of screws and, for this purpose, passes at least partially through an opening in the radially external wall that leads into the combustion chamber. The opening can be sealed around the temperature probe with a suitable material. The measuring probe is connected by means of a cable to an electrical connection block that is fixed to the annular housing surrounding the radially external wall.

[0005] However, drilling through the combustion chamber wall can lead, on the one hand, to disturbances in the flow within the combustion chamber and, on the other hand, to significant damage to the material of the radially external wall. Even if the hole is plugged, the combustion chamber wall is damaged and is Inoperative in flight, hence its use only on test turbomachines. Furthermore, with such a setup, only temperature measurements on a test machine are possible.

[0006] Another solution involves using so-called thermal paints that can change color and solidify when the maximum temperature is reached. These paints preserve the physical integrity of the combustion chamber, but are ineffective because they require complete disassembly of the combustion chamber of the test turbomachine. Furthermore, the paint colors can sometimes be contaminated by fine particles in the combustion chamber and may only indicate the maximum temperature, which is not representative of a real-world, full-flight scenario.

[0007] There is therefore a need to resolve all or part of the aforementioned drawbacks. Summary of the invention

[0008] The objective of the present invention is to provide a simple, efficient and economical solution that allows continuous measurements of the temperature of the combustion chamber while preserving its physical integrity.

[0009] We achieve this objective in accordance with the invention by means of a turbomachine module comprising an annular combustion chamber, having at least one wall delimiting at least part of an enclosure and at least one measuring device mounted on the wall, the measuring device comprising a temperature probe mounted on a radially external surface of the wall and an aerodynamically shaped housing which at least partially surrounds the temperature probe, the housing being mounted on the wall.

[0010] Thus, this solution makes it possible to achieve the aforementioned objective. In particular, the temperature probe is installed outside the wall, specifically on the outer surface of the wall that defines a mixing chamber for the fuel and the combustion chamber airflow. This avoids damaging the combustion chamber wall and limits the impact on the airflow circulating around the combustion chamber wall. Such a configuration allows for continuous temperature measurements, particularly in the most critical areas (for example, areas where the combustion chamber wall has perforations or holes), while preserving the integrity of the combustion chamber wall material. This solution can then be used on a turbomachine under actual flight conditions to perform continuous, real-time measurements on the combustion chamber wall.This helps to ensure flight safety and improve. the design of parts, in terms of lifespan, intended to equip the combustion chamber.

[0011] The turbomachine module also includes one or more of the following features, taken alone or in combination: - the temperature probe includes a thermocouple. - the case comprises a first part and a second part which are distinct and which have a complementary shape. - the first part is formed in one piece with the wall or is fixed to the wall using welding or brazing. - the second part is an added piece on the wall and which is fixed to the wall radially externally using welding or brazing. - the first part and the second part are fixed together using welding or brazing. - at least the second part comprises a material having a melting point lower than that of the wall. - the wall includes dilution holes which are arranged in a circumferential row around a central axis of the combustion chamber, the temperature probe being positioned near the dilution holes. - the housing includes an opening through a wall of the housing and through which passes an electrical power cable connecting the temperature probe to an electrical connection block. - - the module includes an annular housing surrounding at least part of the radially external wall and forming a channel with the radially external wall.

[0012] The invention relates to a turbomachine comprising a turbomachine module as above.

[0013] The invention also relates to an aircraft equipped with such a turbomachine. Brief description of the figures

[0014] The invention will be better understood, and other objects, details, features and advantages thereof will become more apparent upon reading the following detailed explanatory description, of embodiments of the invention given by way of purely illustrative and non-limiting examples, with reference to the accompanying schematic drawings in which:

[0015] - Fig. 1 is an axial cross-sectional view of an example of a turbomachine to which the invention applies;

[0016] - Figure 2 represents an example of a turbomachine module comprising a combustion chamber and a measuring device mounted on the combustion chamber according to the invention;

[0017] - Fig. 3 is a perspective view of an example of a mounted measuring device on a radially external wall of a combustion chamber according to the invention;

[0018] - Figure 4 is a partial, cross-sectional view of a measuring device mounted on a radially external wall of a combustion chamber according to the invention; and

[0019] - Figure 5 schematically represents an example of a measuring probe for a measuring device according to the invention. Detailed description of the invention

[0020] In this description, identical or substantially identical elements and / or elements with the same functions are represented by the same numerical references.

[0021] Figure 1 represents a turbomachine 1 intended to be mounted on an aircraft. The aircraft may be an airplane and may comprise a fuselage and wings extending on either side of the fuselage relative to the fuselage axis. One or more turbomachines may be supported by a wing of the aircraft.

[0022] The turbomachine 1 may be a turbojet (for example, a twin-spool turbofan) or a turboprop or a turboshaft engine. The invention generally applies to a turbomachine 1 comprising a fan or a propeller, whether shrouded or unshrouded.

[0023] In [Fig.1], the turbomachine 1 has a longitudinal axis X, which is here the axis of rotation of the rotors of the turbomachine.

[0024] In the present invention, and more generally, the terms "upstream," "downstream," "axial," and "axially" are defined with respect to the gas flow in the turbomachine and with respect to the longitudinal axis X of the turbomachine. Similarly, the terms "radial," "radially," "internal," and "external" are defined with respect to a radial axis Z perpendicular to the longitudinal axis X.

[0025] The turbomachine 1 in this figure, and generally from upstream to downstream, comprises a compressor assembly 2, a combustion chamber 3, and a turbine assembly 4. The turbomachine is, in particular, a twin-spool, twin-flow turbomachine. The compressor assembly 2 here comprises a low-pressure compressor 2a and a high-pressure compressor 2b.

[0026] The turbine assembly 4 here comprises a low-pressure turbine 4a and a high-pressure turbine 4b. The rotors of the low-pressure compressor 2a and the low-pressure turbine 4a are connected to each other by a low-pressure shaft to form a low-pressure unit. The rotors of the high-pressure compressor 2b and the high-pressure turbine 4b are connected, for example, by a high-pressure shaft to form a high-pressure unit.

[0027] Alternatively, the compressor assembly 2 comprises a single low-pressure compressor and the turbine assembly 4 comprises a single low-pressure turbine. Their rotors are connected by a low-pressure shaft.

[0028] A blower 5 or propeller is mounted upstream of the compressor assembly. In the example shown, the blower 5 advantageously, but not exclusively, comprises blower blades 6 which are surrounded, for example, by a blower housing 7. The latter is advantageously supported by a nacelle 8 centered on the longitudinal axis X.

[0029] Advantageously, the airflow F entering the turbomachine 1 is separated into a primary flow Fl circulating in a primary channel 9 and a secondary flow F2 circulating around the primary channel 9. The primary flow Fl passes through the compressor assembly 2, the combustion chamber 3 and the turbine assembly 4. In the example shown, the secondary flow circulates in a secondary channel 10. The latter is advantageously arranged radially outside the primary channel 9 and is partially delimited by the nacelle 8.

[0030] Figure 2 shows, in axial section, an example of a turbomachine module comprising a combustion chamber 3. As is known, a turbomachine is assembled, in its final assembly, by means of modules comprising compressor, combustion chamber, and turbine modules, which are joined together. Each module comprises a fixed element, or stator, which receives a rotating element, or rotor, carrying compressor or turbine blades, depending on whether the module is a compressor or turbine module. The stator is made up, for example, of an assembly of tubular housings which have annular flanges bolted together for attachment.

[0031] The combustion chamber 3 is advantageously located downstream of a primary flow diffuser 11, which is located at the outlet of the compressor assembly 2. The combustion chamber 3 is typically annular. It advantageously, but not exclusively, comprises at least one wall that delimits at least partially an enclosure 18. A mixture of air from the primary flow Fl and fuel is burned, for example, in the enclosure 18. Preferably, the combustion chamber 3 comprises a radially external wall 12 and a radially internal wall 13 extending along a central axis 14. The central axis 14 is advantageously inclined (for example, between 10° and 55°) with respect to the longitudinal axis X.

[0032] The radially external wall 12 and the radially internal wall 13 are connected upstream by a bottom wall 15. The latter includes, for example, at least one opening 16 through which a fuel injector 17 passes and opens in the enclosure 18 which advantageously, but not limitingly, are formed by the radially external wall 12 and the radially internal wall 13. The bottom wall 15 advantageously, but not limitingly, includes at least one light 19 passing through the wall on both sides (along the central axis 14) and allowing the circulation of the primary flow Fl towards the enclosure 18.

[0033] Advantageously, but not exclusively, at least one of the radially external wall 12 and the radially internal wall 13 is connected downstream to a stator housing (not shown) of the turbomachine. The stator housing may be the housing of a low-pressure turbine. Advantageously, but not exclusively, the radially external wall 12 includes at least one cooling hole 20 that passes through it from one side to the other, and preferably transversely. According to the embodiment shown, several cooling holes 20 are provided in the radially external wall 12. The cooling holes 20 are, for example, located at an intermediate portion 21 of the combustion chamber. The combustion chamber 3 is typically composed of two or three parts.

[0034] The combustion chamber 3 includes, for example, a primary part into which the mixture of the compressed primary stream (approximately 500°C) and pressurized fuel from the injector(s) is inserted to create combustion (where the temperature rises to nearly 2500°C), the intermediate part 21 into which cooling air, entering the combustion chamber 3 through the cooling hole(s) 20, cools the combustion gases to a temperature of approximately 2000°C, and a dilution part 25 into which dilution air provides additional "cold" air, allowing, on the one hand, the combustion gases to be cooled to a temperature, for example, of 1200°C and, on the other hand, the temperature of the combustion gas and the pressure of the gas at the outlet of the combustion chamber 3, and preventing overheating.

[0035] The cooling holes 20 are advantageously arranged in at least one row, at least partly circumferentially with respect to the central axis 14 of the combustion chamber 3. The cooling air is injected into the fuel chamber (in particular into the enclosure 18) through the cooling hole or each of the cooling holes 20. Advantageously, but not limitingly, this or these cooling holes 20 is / are also made in the radially internal wall 13. The cooling air can be from the primary flow.

[0036] As shown in [Fig. 2], the turbomachine comprises a housing 22 which is advantageously arranged around the radially external wall 12 and the radially internal wall 13. The housing 22 is arranged at a distance from the radially external wall 12 and the radially internal wall 13. The housing 22 defines, for example with the radially external wall 12 and the radially internal wall 13, a channel 23, annular, in which at least part of the primary flow from the diffuser 11 circulates. The primary flow advantageously enters the combustion chamber 3 via the cooling hole or each of the cooling holes 20. The cooling hole or each of the cooling holes 20 opens both into the channel 23 and into the enclosure 18.

[0037] Advantageously, but not limitingly, the radially external wall 12 includes at least one dilution hole 24 which passes through it on both sides and preferably transversely. According to the embodiment shown, several dilution holes 24 are provided in the radially external wall 12, for example at the level of the dilution section 25 of the combustion chamber 3. The dilution holes 24 are advantageously arranged in at least one row, at least partially circumferentially with respect to the central axis 14 of the combustion chamber 3. The dilution air is injected into the fuel chamber (in particular into the enclosure 18) through the dilution hole or holes 24. Advantageously, but not exclusively, this or these dilution holes 24 are also provided in the radially internal wall 13. The dilution air may originate from the primary flow which circulates, for example, in the channel 23.

[0038] The dilution part 25 is advantageously arranged downstream of the intermediate part 21.

[0039] Advantageously, the radially external wall 12 (in the same way as the radially internal wall) is made of a material selected from a metallic material, a metal alloy, a ceramic material or a ceramic matrix composite material, and any other refractory material. The material of the combustion chamber walls 3 is capable of withstanding high temperatures, such as those exceeding 1200°C. Preferably, the material of the radially external wall 12 and / or the radially internal wall 13 comprises a ceramic.

[0040] The turbomachine includes at least one measuring device 30 for parameters of the turbomachine 1. These recorded parameters make it possible to carry out, for example, a mapping of pressures, temperatures, accelerations, and / or the composition of flows, fluids, etc.

[0041] With reference to [Fig. 3], the measuring device 30 preferably comprises a temperature probe 31. Advantageously, the temperature probe is mounted on one of the radially external walls 12 and internal walls 13 of the combustion chamber 3. Preferably, the temperature probe 31 is mounted on a radially external surface 32 of the radially external wall 12. In this way, the measuring device 30 is not installed inside the enclosure 18 so as not to disturb the combustion of the primary flow and the fuel and not to damage the wall of the combustion chamber 3.

[0042] Advantageously, the measuring device 30 comprises a housing 33 which surrounds or encloses at least partially the temperature probe 31. The housing 33 thus protects the temperature probe 31 from the external environment and in particular from the primary flow which sweeps through the housing 33 preferably in the channel 23. The housing 33 is preferably mounted at least partially on the radially external wall 12.

[0043] The temperature probe 31 is advantageously held inside the housing 33 and at least partially by a wall 34 of the housing 33. In other words, this housing 33 is hollow. The temperature probe 31 is preferably press-fitted inside the housing 33. This press-fitted mounting allows the temperature probe to be held in place by the housing 33, and in particular the tabs described later to be held in place.

[0044] The housing 33 has an aerodynamic shape that does not impede the circulation of the primary flow around the radially external wall 12. In the present invention, the term "aerodynamic shape" means any shape that does not disturb, or only minimally disturbs, the circulation of the primary flow FL. The aerodynamic profile may include an oval or oblong cross-section, a circular shape, or a NACA-type shape or profile (the initials of which stand for "National Advisory Committee for Aeronautics"). The primary flow Fl quickly returns to its initial position or direction of circulation after encountering the housing 33.

[0045] The primary flow Fl is also not disturbed thanks to the small dimensions of the casing 33. For example, the casing 33 may have a length or diameter between 2 and 3 cm. The dimensions may depend on the dimensions of the combustion chamber, which vary from one turbomachine to another. The influence of the casing 33's integration is then negligible compared to the amount of primary flow passing through the channel 23 and used to cool the combustion chamber 3.

[0046] To this end, and advantageously, the casing 33 has a shape of revolution having an axis of revolution 35. The axis of revolution 35 is substantially perpendicular to the central axis 14 of the combustion chamber 3. The casing 33 comprises, for example, a base 36 and a skirt 37 extending from the base 36 along the axis of revolution 35. The base 36 is, for example, in the form of a disk whose median plane is perpendicular to the axis of revolution 35. The skirt 37 has, for example, a circular cross-section centered on the axis of revolution 35. The casing 33 may further comprise an annular collar 38 centered on the axis of revolution. Advantageously, the collar 38 extends the skirt 37.

[0047] With reference to [Fig. 4], the collar 38 advantageously defines an opening 39 leading into the inside of the housing 33 and opposite the bottom 36. The collar 38 is intended to be fixed to the radially external wall 12 or to the radially internal wall Internal 13 of the combustion chamber 3. The bottom 36, the skirt 37 and the collar 38 advantageously form the wall 34 of the casing 33. This aerodynamic shape of the casing 33 avoids impacting the primary flow circulation in the combustion chamber 3. Of course, the casing 33 could have a different shape while still avoiding any impact on the primary flow circulation in the combustion chamber 3.

[0048] According to one embodiment, the housing 33 is formed from a single piece (molded from another material or monolithic). The housing 33 (monolithic) is attached here by welding or brazing to the radially external wall 12, for example at the flange 38. This method of attachment preserves the physical integrity of the radially external wall 12 and is simple to implement. Advantageously, when the attachment is made by brazing, the material of the wall 34 of the housing 33 has a lower melting point than that of the radially external wall 12. The material can be a ceramic or a metal. During welding, the materials of the housing 33 and the radially external wall 12 are similar (and have a similar melting point).

[0049] Advantageously, but not limitingly, the housing 33 is formed of a first part 33a and a second part 33b. This configuration makes it easier to mount the temperature probe 31 inside the housing 33.

[0050] Advantageously, the housing 33 has a height H1 along the axis of revolution 35, which is measured between the radially external surface 32 of the radially external wall 12 (or the radially internal wall 13) and an internal face 40 of the bottom 36 of the housing 33 (in the installed position). The height H1 is advantageously substantially equal (+ / -10%) to a height H2 of the temperature probe 31. To achieve a tight fit, a spring can advantageously be arranged between the housing and the temperature probe 31.

[0051] According to one embodiment, the first part 33a is formed in one piece (made of material or monolithic) with the radially external wall 12 or the radially internal wall 13. This configuration allows a gain in the manufacture of the wall of the combustion chamber 3 and of the housing 33, a gain in the assembly time of the housing 33 and makes it possible to avoid disturbing the circulation of the air flow around the first part 33a of the housing (there is no break in line between the radially external surface 32 and the external surface of the first part 33a of the housing 33).

[0052] In the case of the two-part housing 33, the first part 33a is made, for example, of the same material as the radially external wall 12. The radially external wall 12 and the first part 33a are, for example, produced by the same additive manufacturing process. Preferably, but not exclusively, this additive manufacturing process may be a laser melting process known as The English acronym SLM stands for "Selective Laser Melting," a process that melts powder from the material used to create the single part. The powder can be metallic or refractory. This process allows for the rapid production of complex shapes. Alternatively, the radially external wall 12 and the first part 33a are produced using a single, very economical casting or forging process. These manufacturing processes can also be used to produce the housing 33 as a single piece.

[0053] Alternatively, the first part 33a is an added component that is fixed to the radially external surface 32 of the radially external wall 12 (or the radially internal wall 13). The attachment can be achieved by welding or brazing. As in the monolithic housing embodiment, advantageously, when the attachment is achieved by brazing, the material of the first part 33a has a lower melting point than that of the radially external wall 12. The material can be a ceramic or a metal. During welding, the materials of the first part 33a and the radially external wall 12 are similar.

[0054] The first part 33a is optionally located upstream of the combustion chamber 3 and preferably near or within one of the critical zones of the combustion chamber 3. The intermediate part 21 with the cooling holes 20 can be considered a critical zone because the temperature is high (approximately 2000°C). The first part 33a can be located, for example, at a distance from the axis of a cooling hole 20 of between 1 and 15 cm. Alternatively, the first part 33a (including the temperature probe 31) can be installed upstream or downstream of the intermediate part 21, for example, near the cooling holes 20, preferably at a distance or radius from the axis of a cooling hole 20 of between 1 and 15 cm.According to yet another alternative, several temperature probes 31 with their respective housing 33 can be placed in different areas of the radially external wall 12 or of the radially internal wall 13.

[0055] The first part 33a has an opening 41 which is partially delimited by an edge 42 of the wall of the second part 33a. The opening 41 is also delimited by the radially external surface 32 in the installation configuration. The opening 41 advantageously opens into the interior of the second part 33b, and the temperature probe 31 is installed via this opening 4L.

[0056] Advantageously, the second part 33b allows the housing 33 to be closed to make it airtight so as not to disrupt the measurements with the primary flow circulating outside the housing 33. In other words, the second part 33b is advantageously arranged downstream of the first part 33a. For example, the second part 33b is an added piece which is fixed to the radially external surface of the radially external wall 12.

[0057] In this description, we mean by the expression "added part" a part which is not manufactured by the same manufacturing process as another part.

[0058] Advantageously, the second part 33b is made of a material that exhibits resistance to high temperatures. However, the material of the second part 33b optionally has a melting point that is lower than that of the material of the radially external wall 12. An example of such a material is chosen from refractory materials or metallic materials capable of withstanding temperatures higher than those prevailing in the combustion chamber 3.

[0059] The attachment of the second part 33b to the radially external wall 12 can be achieved by brazing or welding. The physical integrity of the radially external wall 12 is thus preserved.

[0060] The second part 33b advantageously has a similar and / or complementary shape to that of the first part 33a. This facilitates the assembly of the two parts, particularly when they are both add-on parts. The first and second parts 33a, 33b are fixed together, for example, by welding or brazing.

[0061] According to the illustrated embodiment, the first part 33a and the second part 33b each have a semi-circular cross-section, particularly at the skirt portions 37, which is not limiting. The first and second parts are assembled at their respective edges 42, which are defined in a plane including the axis of revolution 35, for example. The rounded shape of the housing 33 would allow the temperature probe 31 to be mounted tightly inside the housing 33. Alternatively, a spring (not shown) would facilitate the tight mounting of the temperature probe. The spring would bear against the skirt 37 of the housing 33 and a portion of the temperature probe 31, as explained previously.

[0062] During assembly, the temperature probe 31 is slid into the first part 33a, which is attached (either by molding or by welding or brazing) to the radially external wall 12 via its opening 41. The second part 33b is then assembled with the first part 33a and attached to the radially external wall 12 to enclose the temperature probe 31. The second part 33b then presses the temperature probe 31 against the radially external wall 12.

[0063] Advantageously, the housing 33 includes an orifice 43 passing through its wall 34 on both sides. The orifice 43 thus opens into the interior of the housing 33. Preferably, the orifice 43 is provided on the second part 33b of the housing 33 so as not to disrupt the circulation of the primary flow in the channel 23. The orifice 43 allows the passage of an electrical power cable 44 (visible on the [Fig.2]) connecting the temperature probe 31 to an electrical connection block 45. The electrical power cable 44 may advantageously include a sheath made of a material such as tungsten which allows resistance to high temperatures.

[0064] According to an embodiment shown in [Fig. 2], the electrical connection block 45 is mounted on the housing 22. The connection block 45 is removably fixed to a radially internal surface 46 of the housing 22 by means, for example, of fasteners (not shown). These fasteners may include screws or other threaded elements, for example, allowing for easy mounting and dismounting.

[0065] Figure 5 illustrates an example of a temperature probe 31. The latter includes, for example, a thermocouple suitable for measuring the temperature of the wall of the combustion chamber 3. The thermocouple is a solution which, on the one hand, can withstand very high temperatures (which is the case for the temperatures prevailing in the combustion chamber 3) and which, on the other hand, is simple to make, to implement and is economical.

[0066] In this embodiment, the temperature probe 31 comprises a first electrical element 47 and a second electrical element 48 which are connected at one of their ends by a junction 50. Each first electrical element 47 and second electrical element 48 comprises a free end which is pressed against the radially external wall 12, and in particular against the radially external surface 32. The wall 34 of the housing 33 allows the elements 47, 48 to be pressed against the radially external wall 12.

[0067] Optionally, the first and second electrical elements 47, 48 are arranged next to each other.

[0068] A third electrical element 49 is connected at one of its ends to the junction 50.

[0069] The first electrical element 47 is made of a material that is different from that of the second electrical element 48. The materials of the first and second electrical elements include, for example, a metallic material or a metallic alloy. The thermocouple may comprise a first electrical element 47 and a second electrical element 28 whose materials include the following pairs: copper / Constantan®, iron / Constantan®, chromium / Alumel®, Nicrosil® / Nisil®, rhodium-platinum / platinum, 30% rhodium-platinum / 6% rhodium-platinum, tungsten / rhenium. By way of preferred example, the first electrical material is made of copper, platinum, 6% rhodium-platinum, or rhenium, and the second electrical material is made of Constantan, rhodium-platinum, 30% rhodium-platinum, or tungsten. The thermocouple, whose first and second electrical elements 47, 48 are made with the pair Made of rhenium-tungsten materials, it can withstand temperatures exceeding, for example, 2500°C.

[0070] Advantageously, the first electrical element 47 has an electrical resistance that is different from that of the second electrical element 48.

[0071] The junction 50 is advantageously fixed to the radially external surface 32 of the radially external wall 12 (or the radially internal wall 13) whose temperature must be measured, for example, by welding or brazing. The junction 50 then forms a hot weld because it is in contact with the radially external wall 12 or internal wall 13 of the combustion chamber 3.

[0072] Advantageously, the junction 50 is protected in a body 51 made of a metallic material or a refractory material such as an ultra-refractory ceramic or a refractory metal or a composite material or a material similar to that of the radially external wall 12 (or radially internal wall 13) of the combustion chamber.

[0073] Conversely, the third electrical element 49 has another end which is fixed, for example, by means of a weld or braze. This fixing is referred to as a cold weld, for example. Advantageously, the third electrical element 49 is fixed to a probe in an area whose temperature is known and considered to be cooler.

[0074] The thermocouple relies on the electrical voltage level generated by the temperature difference between the hot junction (located in the hot environment to be measured) and the cold junction (located in a cold environment where the temperature is known). When the hot junction is exposed to heat, the temperature variations excite the electrons inside each of the first and second electrical elements 47, 48, which then move at different speeds towards the cold zone of each of the first and second electrical elements 47, 48. These electrons then generate a current in each of the first and second electrical elements 47, 48. This potential difference between the two materials of the first and second electrical elements 47, 48 makes it possible to measure the temperature differences with the cold source, whose temperature is known. This is the Seebeck effect.

[0075] Thus, such a temperature probe is robust and allows for the efficient and continuous acquisition of temperature data for the wall of the combustion chamber 3 during its operation in an aircraft flight. These measurements obtained by the temperature probe 31 mounted outside the wall (radially internal or external) of the combustion chamber 3 help ensure flight safety.

Claims

Demands

1. Turbomachine module comprising an annular combustion chamber (3), having at least one wall (12, 13) delimiting at least part of an enclosure (18) and at least one measuring device (30) mounted on the wall (12, 13), characterized in that the measuring device (30) comprises a temperature probe (31) mounted on a radially external surface (32) of the wall (12, 13) and an aerodynamically shaped housing (33) which at least partially surrounds the temperature probe (31), the housing (33) being mounted on the wall (12, 13).

2. Turbomachine module according to claim 1, characterized in that the temperature probe (31) comprises a thermocouple.

3. Turbomachine module according to claim 1 or 2, characterized in that the housing (33) comprises a first part (33a) and a second part (33b) which are distinct and which have a complementary shape.

4. Turbomachine module according to claim 3, characterized in that the first part (33a) is formed in one piece with the wall (12, 13) or is fixed by means of a weld or braze, on the wall (12, 13).

5. Turbomachine module according to claim 3 or 4, characterized in that the second part (33b) is an added piece on the wall (12, 13) and which is fixed to the wall (12, 13) by means of a weld or a braze.

6. Turbomachine module according to any one of claims 3 to 5, characterized in that the first part (33a) and the second part (33b) are fixed together using welding or brazing.

7. Turbomachine module according to any one of claims 3 to 5, characterized in that at least the second part (33b) comprises a material having a melting temperature lower than that of the wall (12, 13).

8. Turbomachine module according to any one of the preceding claims, characterized in that the wall (12, 13) includes dilution holes (24) which are arranged in a circumferential row with respect to a central axis (14) of the combustion chamber (3), the temperature probe (31) being disposed near the dilution holes (24).

9. Turbomachine module according to any one of the preceding claims, characterized in that the housing (33) includes an opening (43) through a wall (34) of the housing (33) and through which passes an electrical power cable (44) connecting the temperature probe (31) to an electrical connection block (45).

10. Turbomachine (1) comprising a turbomachine module according to any one of the preceding claims.

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