Optical test structure for cooling effect test of turbine blade of aero-engine

Abstract

The invention relates to the technical field of aero-engine tests, in particular to an aero-engine turbine blade cooling effect test optical test structure which comprises optical glass, an outer casing and an optical channel pipe. The optical glass is located on the light-in side of the optical channel pipe, and the light-out side of the optical channel pipe faces the target blade. The outer casing is arranged on the outer side of the optical channel pipe in a sleeving mode, and a cooling channel is formed between the inner wall of the outer casing and the outer wall of the optical channel pipe so as to cool the optical channel pipe; a gas film ring is connected between the optical glass base and the light inlet side of the optical channel pipe in a sealed mode and located on the light outlet side of the optical glass. The optical glass base is provided with the cooling gas inlet, and the gas film ring is provided with the gas jet hole, so that the cooling gas performs jet sweeping on the light emitting surface of the optical glass and enters the optical channel pipe to cool the optical channel pipe, thereby improving the accuracy of the cooling effect test result of the turbine blade.

Description

Technical Field

[0001] The present disclosure relates to the technical field of aero-engine test technology, and in particular to an optical test structure for the cold efficiency test of aero-engine turbine blades. Background Art

[0002] As an important hot-end power output component of an aero-engine, the turbine blade works in a high-temperature and high-pressure environment for a long time, and is prone to damage and failure, thus threatening the normal operation of the engine. Therefore, it is necessary to test the cooling effect of the turbine blade under high-temperature and high-pressure conditions, and measure its temperature distribution under working conditions, etc., to ensure its stability and durability under extreme working conditions, thereby ensuring the overall reliability and safety of the engine.

[0003] The related technologies mainly adopt the infrared-optical test method to determine the temperature field on the blade surface by the infrared radiation characteristics on the surface of the turbine blade under high-temperature and high-pressure operating conditions, or adopt the fluorescence-optical test method to determine the temperature field on the blade surface by actively laser-exciting the fluorescence intensity on the surface of the turbine blade. However, the high-temperature and high-pressure operating environment of the aero-engine turbine blade cooling effect test will cause high-intensity heat conduction to the optical path, resulting in optical test noise in the optical path, weakening or masking the infrared or fluorescence and other optical characteristics of the target blade, and further affecting the accuracy of the blade cold efficiency test results. Summary of the Invention

[0004] In order to solve the above technical problems or at least partially solve the above technical problems, the present disclosure provides an optical test structure for the cold efficiency test of aero-engine turbine blades to improve the accuracy of the cold efficiency test results of the turbine blades.

[0005] The present disclosure provides an optical test structure for the cold efficiency test of aero-engine turbine blades, including an optical glass, an outer casing, and an optical channel tube; The optical glass is located on the light-incident side of the optical channel tube. An optical glass base is provided on the light-incident side of the optical channel tube. The optical glass is disposed on the optical glass base. The light-emitting side of the optical channel tube faces the target blade; The outer casing is sleeved outside the optical channel tube. A cooling channel for the cooling medium to flow is formed between the inner wall of the outer casing and the outer wall of the optical channel tube. And a cooling medium inlet and a cooling medium outlet respectively communicating with the cooling channel are provided on the outer casing to cool the optical channel tube; An air film ring is sealed between the optical glass base and the light incident side of the optical channel tube, and the air film ring is located on the light emitting side of the optical glass; a cooling gas inlet is provided on the optical glass base, and the air film ring has gas jet holes which are respectively connected with the cooling gas inlet and the inner cavity of the optical channel tube, so that the cooling gas can sweep the light emitting surface of the optical glass, and the cooling gas can enter the optical channel tube to cool the optical channel tube.

[0006] Optionally, the cooling channel is provided with spiral ribs extending in a spiral direction along the axial direction of the optical channel tube, so that the cooling channel is formed into a spiral cooling channel for the cooling medium to flow.

[0007] Optionally, the spiral ribs are integrally formed with the outer casing.

[0008] Optionally, the cooling medium inlet is arranged close to the light incident side of the optical channel tube; The cooling medium outlet is arranged close to the light emitting side of the optical channel tube.

[0009] Optionally, an air supply and pressure stabilizing cavity is defined between the air film ring and the optical glass base, and the air supply and pressure stabilizing cavity is communicated with the inner cavity of the optical channel tube.

[0010] Optionally, it also includes a ring-shaped optical glass pressing member; The optical glass pressing piece is located on a side of the optical glass away from the optical glass base, so as to press the optical glass onto the optical glass base.

[0011] Optionally, the optical glass pressing piece is detachably connected to the optical glass base; And / or, a first positioning groove is provided on the side of the optical glass base facing the optical glass pressing piece, and a second positioning groove is provided on the side of the optical glass pressing piece facing the optical glass base, the first positioning groove and the second positioning groove jointly define a positioning groove, and the optical glass is located in the positioning groove.

[0012] Optionally, a flexible graphite ring is arranged between the optical glass pressing member and the optical glass, and the flexible graphite ring is arranged circumferentially along the outer edge of the optical glass; And / or, a flexible graphite ring is arranged between the optical glass and the optical glass base, and the flexible graphite ring is arranged circumferentially along the outer edge of the optical glass.

[0013] Optionally, an optical fiber transmission device is also provided on the light incident side of the optical glass.

[0014] Optionally, it further includes a protective cover which is detachably arranged on the light incident side of the optical glass.

[0015] The optical test structure for the cold efficiency test of the aero-engine turbine blade provided by the embodiment of the present disclosure, by arranging an optical glass, an outer casing and an optical channel tube, the outer casing is sleeved outside the optical channel tube, and a cooling channel is formed between the inner wall of the outer casing and the outer wall of the optical channel tube, so that the cooling medium enters the cooling channel from the cooling medium inlet on the outer casing and exchanges heat with the tube wall of the optical channel tube, thereby cooling the inner cavity of the optical channel tube and reducing the temperature inside the optical channel tube; at the same time, an optical glass base for carrying the optical glass is arranged on the light incident side of the optical channel tube, and a cooling gas inlet is arranged on the optical glass base, and a gas film ring is hermetically connected between the optical glass base and the light incident side of the optical channel tube, so that the cooling gas sequentially enters the inner cavity of the optical channel tube through the cooling gas inlet on the optical glass base and the gas jet holes on the gas film ring, cooling the inner cavity of the optical channel tube and reducing the temperature inside the optical channel tube. That is to say, the inner cavity of the optical channel tube is cooled by the cooling channel outside the optical channel tube and the cooling gas entering the inner cavity of the optical channel tube together, realizing double cooling and temperature reduction of the inner cavity of the optical channel tube, so that the inner cavity of the optical channel tube obtains a continuous cooling operation environment, thereby weakening to a certain extent the optical test noise generated by the heat conduction of the optical path due to the high-temperature and high-pressure operating environment, and further avoiding the interference of optical noise on the optical characteristics of the target blade to a certain extent, improving the accuracy of the blade cold efficiency test result, and providing accurate and effective data support for the engine test research.

[0016] At the same time, since the gas film ring is hermetically connected between the optical glass base and the light incident side of the optical channel tube, and the gas film ring is located on the light exit side of the optical glass, after the cooling gas entering from the cooling gas inlet of the optical glass base is ejected through the gas jet holes on the gas film ring, the air flow can sweep the light exit surface of the optical glass, thereby avoiding to a certain extent the situation that tiny carbide particles in the high-speed gas in the main gas channel of the engine fly into the inner cavity of the optical channel tube and contaminate the optical glass, improving the cleanliness of the optical glass, and providing a guarantee for the accuracy of the test result.

[0017] It is to be understood that both the foregoing general description and the following detailed description are exemplary and are intended to provide further explanation of the claimed technology. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The above and other objects, features, and advantages of the present disclosure will become more apparent by describing the embodiments of the present disclosure in more detail with reference to the accompanying drawings. The accompanying drawings are used to provide a further understanding of the embodiments of the present disclosure and constitute a part of the specification. Together with the embodiments of the present disclosure, they are used to explain the present disclosure and do not constitute a limitation to the present disclosure. In the drawings, the same reference numerals generally represent the same components or steps.

[0019] Figure 1 Schematic structural diagram of an optical test structure for cold efficiency test of an aeroengine turbine blade provided by an embodiment of the present disclosure; Figure 2 is Figure 1 sectional view taken along line A-A in Figure 3 Schematic diagram of the flow directions of the cooling medium and the cooling gas in the optical test structure for cold efficiency test of an aeroengine turbine blade provided by an embodiment of the present disclosure; Figure 4 Schematic diagram of the structural state when the optical test structure for cold efficiency test of an aeroengine turbine blade provided by an embodiment of the present disclosure is performing a cold efficiency test on the engine turbine blade.

[0020] Wherein, 1. optical glass; 2. optical glass base; 21. cooling gas inlet; 22. first positioning groove; 3. outer casing; 31. cooling channel; 311. cooling medium inlet; 312. cooling medium outlet; 313. spiral rib; 4. optical channel tube; 5. air film ring; 51. air supply pressure stabilizing cavity; 6. optical glass pressing member; 61. fastener; 62. second positioning groove; 7. flexible graphite ring; 8. optical fiber conduction device; 9. protective cover; 100. light source; 200. blade; 300. combustion chamber. Detailed implementation manners

[0021] In order to make the purpose, technical solutions, and advantages of the present disclosure more obvious, exemplary embodiments according to the present disclosure will be described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present disclosure, rather than all the embodiments of the present disclosure. It should be understood that the present disclosure is not limited by the exemplary embodiments described herein.

[0022] The term "including" and its variations used in this document are open inclusions, that is, "including but not limited to". The term "based on" means "based at least in part on". The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one other embodiment"; the term "some embodiments" means "at least some embodiments". Relevant definitions of other terms will be given in the description below. It should be noted that the concepts of "first", "second", etc. mentioned in this disclosure are only used to distinguish different devices, modules or units, and are not used to limit the order or interdependence of the functions performed by these devices, modules or units.

[0023] It should be noted that the modifications of "one" and "plurality" mentioned in the present disclosure are illustrative rather than restrictive, and those skilled in the art should understand that unless otherwise clearly indicated in the context, it should be understood as "one or more".

[0024] As turbine blades are important hot-end power output components of aircraft engines, they work under high temperature and high pressure for a long time and are prone to damage and failure, thus threatening the normal operation of the engine. Therefore, it is necessary to test the turbine blades by measuring their temperature distribution under working conditions to ensure their stability and durability under extreme working conditions, thereby ensuring the overall reliability and safety of the engine.

[0025] Specifically, the cooling effect test of turbine blades can be carried out through optical testing methods such as infrared or fluorescence. However, the high temperature and high pressure operating environment of the cooling effect test of aircraft engine turbine blades will cause high-intensity heat conduction to the optical path, resulting in optical test noise in the optical path. The optical test noise will weaken or mask the optical characteristics of the target blades such as infrared or fluorescence, thereby affecting the accuracy of the blade cooling effect test results.

[0026] Based on this, the embodiment of the present disclosure provides an optical test structure for the cooling efficiency test of an aircraft engine turbine blade to improve the accuracy of the blade cooling efficiency test results. The optical test structure for the cooling efficiency test of an aircraft engine turbine blade provided by the present disclosure is described in detail through specific embodiments in conjunction with the accompanying drawings: Reference Figures 1 to 4 As shown, an embodiment of the present disclosure provides an optical test structure for a cold effect test of an aircraft engine turbine blade, which is specifically used to perform a cold effect test on an engine turbine blade.

[0027] The aircraft engine specifically includes a compressor, a combustion chamber 300, a turbine and a tail nozzle. The compressor is used to compress the air. The compressed air is mixed with fuel and burned in the combustion chamber 300 to generate high-temperature and high-pressure combustion gas. The high-temperature and high-pressure combustion gas drives the turbine blades 200 to rotate, so that the combustion gas is ejected through the tail nozzle to provide thrust for the aircraft to fly.

[0028] The optical test structure for the cold efficiency test of an aero-engine turbine blade provided by an embodiment of the present disclosure includes an optical glass 1 and an optical channel tube 4.

[0029] The optical glass 1 is located on the light incident side of the optical channel tube 4. An optical glass base 2 is provided on the light incident side of the optical channel tube 4. The optical glass 1 is arranged on the optical glass base 2. The light exit side of the optical channel tube 4 faces the target blade 200.

[0030] Refer to Figure 4 As shown, in specific implementation, the test light source 100 is placed on the light incident side of the optical glass 1. The light source 100 can be, for example, an infrared light source or a fluorescent light source. The embodiments of the present disclosure are not limited thereto, as long as it can provide a test light source. The light emitted by the light source 100 enters from the light incident side of the optical glass 1, exits from the light exit side of the optical glass 1, and enters the optical channel tube 4. The inner cavity of the optical channel tube 4 forms an optical path. The light finally exits onto the target blade 200. By collecting the optical characteristics of the target blade 200, the temperature distribution parameters of the blade can be obtained, etc. By analyzing these parameters, the stability and durability of the blade 200 under extreme working conditions can be ensured, thereby guaranteeing the overall reliability and safety of the engine.

[0031] The optical test structure for the cold efficiency test of an aero-engine turbine blade further includes an outer casing 3 and an air film ring 5. Among them, the outer casing 3 is sleeved outside the optical channel tube 4. A cooling channel 31 for the flow of a cooling medium is formed between the inner wall of the outer casing 3 and the outer wall of the optical channel tube 4. And cooling medium inlets 311 and cooling medium outlets 312 respectively communicating with the cooling channel 31 are provided on the outer casing 3 to cool the optical channel tube 4.

[0032] In specific implementation, the cooling medium inlet 311 can be communicated with an external cooling medium supply container to provide a cooling medium for the cooling channel 31 through the cooling medium supply container. The cooling medium enters the cooling channel 31 from the cooling medium inlet 311, flows in the cooling channel 31, exchanges heat with the optical channel tube 4, takes away the heat of the tube wall of the optical channel tube 4, and the cooling medium that absorbs heat finally flows out from the cooling medium outlet 312. Refer to Figure 3 As shown, the flow direction of the cooling medium can be, for example, Figure 3 the direction indicated by the solid line arrow shown, so as to realize the cooling of the optical channel tube 4, and further realize the cooling and temperature reduction of the inner cavity of the optical channel tube 4, absorb the heat conducted by the high-temperature and high-pressure operating environment of the engine to the inner cavity of the optical channel tube 4, and to a certain extent avoid generating optical test noise in the optical path in the inner cavity of the optical channel tube 4.

[0033] Exemplarily, the above cooling medium can specifically be cooling water.

[0034] Of course, in other implementation manners, the above cooling medium may also be other cooling liquids, such as liquid metal, oil-water mixture, or emulsified coolant, etc. Or it may also be a cooling gas, as long as it can flow in the cooling channel 31 to achieve the cooling of the optical channel tube 4.

[0035] Among them, the gas film ring 5 is sealingly connected between the optical glass base 2 and the light incident side of the optical channel tube 4, and the gas film ring 5 is located on the light emitting side of the optical glass 1. Specifically, a cooling gas inlet 21 is provided on the optical glass base 2, and the gas film ring 5 has gas jet holes respectively communicating with the cooling gas inlet 21 and the inner cavity of the optical channel tube 4, so that the cooling gas jets and sweeps the light emitting surface of the optical glass 1, and the cooling gas enters the optical channel tube 4 to cool the optical channel tube 4.

[0036] Exemplarily, the optical glass base 2 may be annular, for example. The optical glass base 2 and the optical channel tube 4 are coaxially arranged. It can be understood that the inner ring diameter of the optical glass base 2 is not less than the inner diameter of the optical channel tube 4 to ensure the normal transmission of light. Of course, in other implementation manners, the optical glass base 2 may not be annular, as long as it can effectively carry the optical glass 1, and the projection of the optical glass base 2 in the axial direction is located outside the projection of the optical channel tube 4 in the axial direction without blocking the light.

[0037] Similarly, the projection of the gas film ring 5 in the axial direction is located outside the projection of the optical channel tube 4 in the axial direction without blocking the light, ensuring the effective transmission of light.

[0038] In specific implementation, the cooling gas inlet 21 can be connected to an air cooling pipe, and the cooling gas is introduced into the cooling gas inlet 21 through the air cooling pipe. Exemplarily, the cooling gas inlet 21 can be installed together with the air cooling pipe by means of threaded connection. For example, a channel communicating with the cooling gas inlet 21 is provided on the optical glass base 2. The channel inlet communicates with the cooling gas inlet 21, and the channel outlet communicates with the gas jet holes of the gas film ring 5. The cooling gas entering from the cooling gas inlet 21 is ejected through the gas jet holes and then enters the optical channel tube 4 to cool the inner cavity of the optical channel tube 4. Refer to Figure 3 As shown, the flow direction of the cooling gas can be, for example, Figure 3 the direction indicated by the dotted arrow shown.

[0039] Moreover, since the gas film ring 5 is located on the light-emitting side of the optical glass 1, the cooling gas ejected from the gas jet holes can also sweep the light-emitting surface of the optical glass 1. If tiny carbide particles in the high-speed combustion gas in the main combustion gas passage of the engine accidentally fly into the optical channel tube 4, the light-emitting surface of the optical glass 1 is jet-swept by the cooling gas to clean the optical glass 1, avoiding particulate matter contamination of the optical glass 1. While protecting the optical glass 1, the test accuracy is improved.

[0040] Since the cooling medium introduced into the inner cavity of the optical channel tube 4 is a gas, compared with the scheme of introducing a cooling liquid into the inner cavity of the optical channel tube 4, the cooling gas will not affect the optical path. Specifically, the cooling gas can be, for example, air, or a gas with different temperature levels and different components.

[0041] Exemplarily, one cooling gas inlet 21 can be provided on the optical glass base 2, or multiple cooling gas inlets 21 can be provided. For example, the multiple cooling gas inlets 21 are arranged at intervals along the circumference of the optical glass 1, so that the cooling gas is introduced simultaneously from multiple positions in the circumferential direction, improving the cooling effect and cooling efficiency.

[0042] Specifically, the pressure and flow rate of the cooling gas and the cooling medium can be adjusted according to actual needs, or the cooling gas and the cooling medium can be supplied at a constant pressure. For example, a controller is provided to adjust the pressure and flow rate of the cooling gas and the cooling medium.

[0043] Among them, the cooling gas and the cooling medium can be recycled to reduce the test cost.

[0044] The optical test structure for the cold efficiency test of an aero-engine turbine blade provided by the embodiments of the present disclosure sets an optical glass 1, an outer casing 3, and an optical channel tube 4. The outer casing 3 is sleeved outside the optical channel tube 4, and a cooling channel 31 is formed between the inner wall of the outer casing 3 and the outer wall of the optical channel tube 4. The cooling medium enters the cooling channel 31 from the cooling medium inlet 311 on the outer casing 3 and exchanges heat with the tube wall of the optical channel tube 4, thereby cooling the inner cavity of the optical channel tube 4 and reducing the temperature inside the optical channel tube 4. At the same time, an optical glass base 2 for carrying the optical glass 1 is provided on the light incident side of the optical channel tube 4, a cooling gas inlet 21 is provided on the optical glass base 2, and an air film ring 5 is hermetically connected between the optical glass base 2 and the light incident side of the optical channel tube 4. The cooling gas sequentially enters the inner cavity of the optical channel tube 4 through the cooling gas inlet 21 on the optical glass base 2 and the gas jet holes on the air film ring 5, cooling the inner cavity of the optical channel tube 4 and reducing the temperature inside the optical channel tube 4. That is to say, the inner cavity of the optical channel tube 4 is cooled by the cooling channel 31 outside the optical channel tube 4 and the cooling gas entering the inner cavity of the optical channel tube 4, realizing double cooling and temperature reduction of the inner cavity of the optical channel tube 4, so that the inner cavity of the optical channel tube 4 obtains a continuous cooling operation environment, thereby weakening to a certain extent the optical test noise generated by the heat conduction of the optical path due to the high-temperature and high-pressure operation environment, and further avoiding the interference of optical noise on the optical characteristics of the target blade to a certain extent, improving the accuracy of the blade cold efficiency test result, and providing accurate and effective data support for engine test research.

[0045] At the same time, since the air film ring 5 is hermetically connected between the optical glass base 2 and the light incident side of the optical channel tube 4, and the air film ring 5 is located on the light exit side of the optical glass 1, after the cooling gas entering from the cooling gas inlet 21 of the optical glass base 2 is ejected through the gas jet holes on the air film ring 5, the air flow can sweep the light exit surface of the optical glass 1, thereby avoiding to a certain extent the situation that tiny carbide particles in the high-speed gas in the main gas channel of the engine fly into the inner cavity of the optical channel tube 4 and contaminate the optical glass 1, improving the cleanliness of the optical glass 1, and providing a guarantee for the accuracy of the test result.

[0046] When specifically implemented, a temperature-resistant antireflection film can be provided on the light incident surface of the optical glass 1, thereby improving the light penetration ability and further improving the accuracy of the test result.

[0047] Continue to refer to Figure 2 and Figure 3 As shown in the figure, in some embodiments, spiral ribs 313 extending spirally along the axial direction of the optical channel tube 4 are provided in the cooling channel 31, so that the cooling channel 31 is formed into a spiral cooling channel 31 for the cooling medium to flow.

[0048] This arrangement extends the flow path length of the cooling medium while keeping the outer contour dimensions of the optical channel tube 4 and the outer casing 3 unchanged, thereby further improving the cooling efficiency and cooling effect of the optical channel tube 4, and further improving the test efficiency and test accuracy.

[0049] In some embodiments, the spiral ribs 313 may be integrally formed with the outer casing 3. This improves the overall structural strength of the spiral ribs 313 and the outer casing 3 to a certain extent.

[0050] In other implementations, the spiral ribs 313 and the optical channel tube 4 may be integrally formed, or the optical channel tube 4 , the spiral ribs 313 and the outer casing 3 may be integrally formed.

[0051] Combination Figures 1 to 3 As shown, in some embodiments, the cooling medium inlet 311 is disposed close to the light incident side of the optical channel tube 4 , and the cooling medium outlet 312 is disposed close to the light exit side of the optical channel tube 4 .

[0052] This increases the contact area between the cooling medium and the tube wall of the optical channel tube 4, thereby improving the cooling efficiency and cooling effect of the optical channel tube 4. This can also avoid the situation where the cooling medium flowing in from the cooling medium inlet 311 is directly discharged from the cooling medium outlet 312 before fully exchanging heat with the tube wall of the optical channel tube 4, further improving the cooling efficiency and cooling effect.

[0053] Reference Figure 2 As shown, in some embodiments, an air supply and pressure stabilizing cavity 51 is defined between the air film ring 5 and the optical glass base 2 , and the air supply and pressure stabilizing cavity 51 is communicated with the inner cavity of the optical channel tube 4 .

[0054] In this way, the cooling gas entering from the cooling gas inlet 21 is buffered in the gas supply pressure stabilizing chamber 51, thereby further ensuring the stability of the pressure in the optical channel tube 4 and the flow of the cooling gas, and further providing a guarantee for the accuracy of the test results.

[0055] Continue to refer to Figures 1 to 4 As shown, in some embodiments, the optical test structure for cooling effect test of aircraft engine turbine blades provided by the embodiments of the present disclosure further includes an annular optical glass pressing member 6. The optical glass pressing member 6 is located on the side of the optical glass 1 away from the optical glass base 2 to press the optical glass 1 onto the optical glass base 2.

[0056] By providing the optical glass pressing member 6 , the stability of the optical glass 1 is further improved, thereby further ensuring the stability of the optical transmission path, and further improving the accuracy of the test results.

[0057] It can be understood that the axial projection of the optical glass pressing member 6 is located outside the axial projection of the optical channel tube 4, so that the optical glass pressing member 6 does not interfere with the normal transmission of light.

[0058] In some embodiments, the optical glass pressing member 6 and the optical glass base 2 can be connected in a detachable manner.

[0059] Referring to Figure 2 As shown, for example, mounting holes are provided on both the optical glass pressing member 6 and the optical glass base 2, and the optical glass pressing member 6 and the optical glass base 2 are connected together by a fastener 61 passing through the corresponding mounting holes. The fastener 61 can be, for example, a fastening bolt or the like.

[0060] For another example, the optical glass pressing member 6 and the optical glass base 2 can also be detachably connected together by snap-fitting of an elastic snap and a snap hole.

[0061] With such a setting, when the optical glass 1 needs to be replaced, repaired, etc., it is only necessary to detach the optical glass pressing member 6 and the optical glass base 2, which improves the convenience of replacing or repairing the optical glass 1. Moreover, when one of the optical glass pressing member 6 and the optical glass base 2 is damaged, the two are detached, and only the damaged part needs to be replaced, avoiding the scrapping of the overall structure and saving costs. Combined with Figures 2 to 4 As shown, in some embodiments, a first positioning groove 22 is provided on the side of the optical glass base 2 facing the optical glass pressing member 6, and a second positioning groove 62 is provided on the side of the optical glass pressing member 6 facing the optical glass base 2. The first positioning groove 22 and the second positioning groove 62 jointly define a positioning groove, and the optical glass 1 is located in the positioning groove.

[0062] With such a setting, reliable positioning of the optical glass 1 is achieved, further improving the stability of the optical glass 1, thus ensuring the smooth progress of the test process and further improving the accuracy of the test results.

[0063] In some embodiments, a flexible graphite ring 7 is provided between the optical glass pressing member 6 and the optical glass 1, and the flexible graphite ring 7 is circumferentially arranged along the outer edge of the optical glass 1. A flexible graphite ring 7 can also be provided between the optical glass 1 and the optical glass base 2, and the flexible graphite ring 7 is circumferentially arranged along the outer edge of the optical glass 1.

[0064] It can be understood that the flexible graphite ring 7 is arranged along the outer edge of the optical glass 1, that is, the axial projection of the flexible graphite ring 7 is located outside the axial projection of the optical channel tube 4, so that the flexible graphite ring 7 does not block the light, ensuring the normal and effective transmission of light.

[0065] By setting the flexible graphite ring 7, the optical glass 1 can be protected to a certain extent, and the vibration generated during the test can be effectively buffered, thereby improving the accuracy of the test results.

[0066] In some embodiments, the optical test structure for the cold efficiency test of an aero-engine turbine blade further includes a protective cover 9, which is detachably disposed on the light incident side of the optical glass 1.

[0067] When the test is over or not carried out, the protective cover 9 is disposed on the light incident side of the optical glass 1, so as to effectively protect the optical glass 1, avoid the situation that the optical glass 1 is contaminated or damaged, provide guarantee for accurate test, and facilitate the handling or movement of the optical test structure for the cold efficiency test of the blade.

[0068] Specifically, for example, the optical glass pressing member 6 is annular, and a protrusion is provided on the side of the protective cover 9 facing the optical glass 1. The protrusion exactly matches the annular inner cavity of the optical glass pressing member 6. When the protective cover 9 is disposed on the light incident side of the optical glass 1, the protrusion exactly extends into the annular inner cavity of the optical glass pressing member 6 to achieve matching covering.

[0069] For another example, the protective cover 9 includes a cover body and an annular cap edge disposed along the circumference of the cover body. The cover body is disposed on the light incident side of the optical glass 1, and the annular cap edge surrounds the outside of the optical glass base 2.

[0070] Continue to refer to Figure 2 As shown, in some embodiments, an optical fiber conduction device 8 may also be disposed on the light incident side of the optical glass 1.

[0071] By setting the optical fiber conduction device 8, the stability and reliability of light input are further improved, and the applicable range of the optical test structure for the cold efficiency test of an aero-engine turbine blade provided by the embodiments of the present disclosure is further expanded.

[0072] During specific tests, by way of example, the mainstream gas indicators are: pressure 1.5 MPa, flow rate 6.8 kg / s, and temperature 1600 K. The optical test structure for the cold efficiency test of an aero-engine turbine blade provided by the embodiments of the present disclosure can keep the optical path at a constant temperature stably, greatly reduce the optical noise, will not generate optical signals that block or interfere with the optical characteristics of the target blade, and will not have the phenomenon that the main gas tiny carbonized particles contaminate the optical lens, and works stably and reliably.

[0073] The optical test structure for the cold efficiency test of an aero-engine turbine blade provided by an embodiment of the present disclosure provides structural support for the optical test (such as infrared optics, excited fluorescence, etc.) of the wall temperature fields of characteristic parts such as the leading edge, trailing edge, blade basin, and blade back in the equivalent full-engine high-temperature and high-pressure cooling effect test of an aero-engine turbine blade. It can also be used for the molten sand dust erosion test of hot-end components of an aero-engine or the recording of wall deposits or the development of macroscopic cracks in thermal shock / thermal fatigue, providing support for the comparative analysis of the deposition performance and deposition phenomena of the test research object or providing support for the thermal strength analysis of the test research object.

[0074] The optical test structure for the cold efficiency test of an aero-engine turbine blade provided by an embodiment of the present disclosure can broaden the application scope of the optical temperature measurement scheme for engineering iterative design and experimental research verification, weaken the strong optical test noise formed by intense heat conduction and radiation under near or quasi-real operating conditions, and reduce or completely avoid the probability that tiny carbonized particles contaminate the inner wall of the light-transmitting glass on the optical channel, resulting in the weakening or occlusion of the infrared or fluorescence characteristics of the test target body. It can also weaken the interference caused by non-designed expected heat conduction for basic theoretical research in universities, improve the discrimination ability of the influence law and influence weight analysis of boundary condition parameters on research target parameters, and can greatly shorten the on-site preparation time of experimental research or verification, improving experimental efficiency.

[0075] The above description is only some embodiments of the present disclosure and an explanation of the applied technical principles. Those skilled in the art should understand that the disclosed scope in the present disclosure is not limited to the technical solutions formed by the specific combination of the above technical features, and should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the above disclosed concept. For example, the technical solutions formed by mutually replacing the above features with the (but not limited to) technical features with similar functions disclosed in the present disclosure.

[0076] Although some specific embodiments of the present disclosure have been described in detail by way of examples, those skilled in the art should understand that the above examples are only for illustration and not for limiting the scope of the present disclosure. Those skilled in the art should understand that the above embodiments can be modified without departing from the scope and spirit of the present disclosure. The scope of the present disclosure is defined by the appended claims.

Claims

1. An optical test structure for the cold efficiency test of an aeroengine turbine blade, characterized in that Includes optical glass, outer casing and optical channel tube; The optical glass is located at the light incident side of the optical channel tube, an optical glass base is provided at the light incident side of the optical channel tube, the optical glass is provided on the optical glass base, and the light exit side of the optical channel tube faces the target blade; The outer casing is sleeved on the outer side of the optical channel tube, a cooling channel for cooling medium to flow is formed between the inner wall of the outer casing and the outer wall of the optical channel tube, and a cooling medium inlet and a cooling medium outlet respectively connected to the cooling channel are provided on the outer casing to cool the optical channel tube; An air film ring is sealed between the optical glass base and the light incident side of the optical channel tube, and the air film ring is located on the light emitting side of the optical glass; a cooling gas inlet is provided on the optical glass base, and the air film ring has gas jet holes which are respectively connected with the cooling gas inlet and the inner cavity of the optical channel tube, so that the cooling gas can sweep the light emitting surface of the optical glass, and the cooling gas can enter the optical channel tube to cool the optical channel tube.

2. The optical test structure for the cold efficiency test of the aero-engine turbine blade according to claim 1, characterized in that, The cooling channel is provided with spiral ribs extending spirally along the axial direction of the optical channel tube, so that the cooling channel is formed into a spiral cooling channel for the cooling medium to flow.

3. The optical test structure for the cold efficiency test of an aero-engine turbine blade according to claim 2, wherein The spiral ribs are integrally formed with the outer casing.

4. The optical test structure for the cold efficiency test of an aeroengine turbine blade according to claim 1, characterized in that The cooling medium inlet is arranged close to the light incident side of the optical channel tube; The cooling medium outlet is arranged close to the light emitting side of the optical channel tube.

5. The optical test structure for the cold efficiency test of an aeroengine turbine blade according to claim 1, characterized in that, An air supply and pressure stabilizing cavity is defined between the air film ring and the optical glass base, and the air supply and pressure stabilizing cavity is communicated with the inner cavity of the optical channel tube.

6. The optical test structure for the cold efficiency test of an aeroengine turbine blade according to claim 1, wherein Also included is an annular optical glass pressing member; The optical glass pressing piece is located on a side of the optical glass away from the optical glass base, so as to press the optical glass onto the optical glass base.

7. The optical test structure for the cold efficiency test of an aeroengine turbine blade according to claim 6, characterized in that, The optical glass pressing piece is detachably connected to the optical glass base; And / or, a first positioning groove is provided on the side of the optical glass base facing the optical glass pressing piece, and a second positioning groove is provided on the side of the optical glass pressing piece facing the optical glass base, the first positioning groove and the second positioning groove jointly define a positioning groove, and the optical glass is located in the positioning groove.

8. The optical test structure for the cold efficiency test of an aeroengine turbine blade according to claim 6, characterized in that, A flexible graphite ring is arranged between the optical glass pressing member and the optical glass, and the flexible graphite ring is arranged circumferentially along the outer edge of the optical glass; And / or, a flexible graphite ring is arranged between the optical glass and the optical glass base, and the flexible graphite ring is arranged circumferentially along the outer edge of the optical glass.

9. The optical test structure for the cold efficiency test of an aeroengine turbine blade according to any one of claims 1 to 8, characterized in that, An optical fiber transmission device is also provided on the light incident side of the optical glass.

10. The optical test structure for cold efficiency test of an aeroengine turbine blade according to any one of claims 1 to 8, characterized in that, It also includes a protective cover, which is a detachable cover arranged on the light incident side of the optical glass.

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