Optical test structure for aero-engine turbine blade cold efficiency test

Abstract

The present disclosure relates to the technical field of aero-engine test, and particularly provides an optical test structure for aero-engine turbine blade cold efficiency test, comprising optical glass, an outer casing and an optical channel pipe; the optical glass is located at an incident light side of the optical channel pipe, and an outgoing light side of the optical channel pipe faces a target blade; the outer casing is sleeved on an outer side of the optical channel pipe, a cooling channel is formed between an inner wall of the outer casing and an outer wall of the optical channel pipe to cool the optical channel pipe; an air film ring is sealingly connected between an optical glass base and the incident light side of the optical channel pipe, and the air film ring is located at an outgoing light side of the optical glass; the optical glass base is provided with a cooling gas inlet, and the air film ring is provided with gas jet holes, so that the cooling gas performs jet sweeping on an outgoing light surface of the optical glass, and the cooling gas enters into the optical channel pipe to cool the optical channel pipe, thereby improving the accuracy of the turbine blade cold efficiency test result.

Description

TECHNICAL FIELD

[0001] The present disclosure relates to the technical field of aero-engine test, in particular to an optical test structure for aero-engine turbine blade cold efficiency test. BACKGROUND

[0002] Turbine blades are important heat-end power output components of aero-engines, which work in a high-temperature and high-pressure environment for a long time, and are prone to damage and failure, thereby threatening the normal operation of the engine. Therefore, the cooling effect of the turbine blade under high-temperature and high-pressure conditions needs to be tested, and the temperature distribution and the like under the working state are measured to ensure the stability and durability of the turbine blade under extreme working conditions, thereby ensuring the overall reliability and safety of the engine.

[0003] The related art mainly adopts an infrared-optical test method of determining the turbine blade surface temperature field by using the infrared radiation characteristics of the turbine blade surface under high-temperature and high-pressure operating conditions, or a fluorescence-optical test method of determining the turbine blade surface temperature field by using the fluorescence intensity of the turbine blade surface excited by an active laser. However, the high-temperature and high-pressure operating environment of the aero-engine turbine blade cooling effect test causes high-intensity heat conduction to the optical path, resulting in optical test noise in the optical path, weakening or masking the infrared or fluorescence optical characteristics of the target blade, and further affecting the accuracy of the blade cold efficiency test results. SUMMARY

[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 aero-engine turbine blade cold efficiency test to improve the accuracy of turbine blade cold efficiency test results.

[0005] The present disclosure provides an optical test structure for aero-engine turbine blade cold efficiency test, comprising optical glass, an outer casing and an optical channel pipe.

[0006] The optical glass is located on the light-in side of the optical channel pipe, the light-in side of the optical channel pipe is provided with an optical glass base, the optical glass is arranged on the optical glass base, and the light-out side of the optical channel pipe faces the target blade.

[0007] The outer casing is sleeved on the outside of the optical channel pipe, 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 pipe, and a cooling medium inlet and a cooling medium outlet are formed on the outer casing and communicate with the cooling channel, respectively, to cool the optical channel pipe.

[0008] The gas film ring is located at the light emitting side of the optical glass, and the optical glass base is provided with a cooling gas inlet, and the gas film ring is provided with gas jet holes respectively communicating with the cooling gas inlet and the inner cavity of the optical channel tube, so that the cooling gas performs jet sweeping on the light emitting surface of the optical glass, and the cooling gas enters the optical channel tube to cool the optical channel tube.

[0009] Optionally, the cooling channel is provided with a spiral rib extending 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.

[0010] Optionally, the spiral rib is integrally formed with the outer casing.

[0011] Optionally, the cooling medium inlet is arranged close to the light entering side of the optical channel tube.

[0012] The cooling medium outlet is arranged close to the light emitting side of the optical channel tube.

[0013] Optionally, a gas supply stable pressure cavity is defined between the gas film ring and the optical glass base, and the gas supply stable pressure cavity communicates with the inner cavity of the optical channel tube.

[0014] Optionally, it further comprises an annular optical glass pressing member.

[0015] The optical glass pressing member is located on the side of the optical glass away from the optical glass base, so as to press the optical glass on the optical glass base.

[0016] Optionally, the optical glass pressing member is detachably connected with the optical glass base.

[0017] And / or, the side of the optical glass base facing the optical glass pressing member is provided with a first positioning groove, and the side of the optical glass pressing member facing the optical glass base is provided with a second positioning groove, and the first positioning groove and the second positioning groove jointly define a positioning groove, and the optical glass is located in the positioning groove.

[0018] Optionally, a flexible graphite ring is arranged between the optical glass pressing member and the optical glass, and the flexible graphite ring is circumferentially arranged along the outer edge of the optical glass.

[0019] And / or, a flexible graphite ring is arranged between the optical glass and the optical glass base, and the flexible graphite ring is circumferentially arranged along the outer edge of the optical glass.

[0020] Optionally, the light entry side of the optical glass is further provided with a fiber transmission device.

[0021] Optionally, the optical glass further comprises a protective cover, which is detachably arranged on the light entry side of the optical glass.

[0022] The optical test structure for the turbine blade cold efficiency test of the aero-engine provided by the embodiment of the present disclosure, by arranging the optical glass, the outer casing and the optical channel pipe, the outer casing is sleeved outside the optical channel pipe, and the cooling channel is formed between the inner wall of the outer casing and the outer wall of the optical channel pipe, the cooling medium enters the cooling channel from the cooling medium inlet on the outer casing, and exchanges heat with the pipe wall of the optical channel pipe, so as to cool the inner cavity of the optical channel pipe and reduce the temperature in the optical channel pipe; at the same time, the optical glass base bearing the optical glass is arranged on the light entry side of the optical channel pipe, the cooling gas inlet is arranged on the optical glass base, and the gas film ring is sealingly connected between the optical glass base and the light entry side of the optical channel pipe, so that the cooling gas enters the optical channel pipe through the cooling gas inlet on the optical glass base and the gas jet hole on the gas film ring in sequence, and cools the inner cavity of the optical channel pipe, thereby reducing the temperature in the optical channel pipe. That is, the inner cavity of the optical channel pipe is cooled by the cooling channel outside the optical channel pipe and the cooling gas entering the inner cavity of the optical channel pipe, so as to realize the double cooling of the inner cavity of the optical channel pipe, so as to obtain a continuous cooling running environment for the inner cavity of the optical channel pipe, thereby weakening the optical test noise caused by the heat conduction of the optical path in the high temperature and high pressure running environment to a certain extent, avoiding the interference of the 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.

[0023] At the same time, since the gas film ring is sealingly connected between the optical glass base and the light entry side of the optical channel pipe, and the gas film ring is located on the light exit side of the optical glass, the cooling gas entering the cooling gas inlet of the optical glass base can sweep the light exit surface of the optical glass after being sprayed out through the gas jet hole on the gas film ring, so as to avoid the small carbon particles in the high-speed gas in the engine main gas passage flying into the inner cavity of the optical channel pipe and polluting the optical glass to a certain extent, and improve the cleanliness of the optical glass, thereby providing a guarantee for the accuracy of the test result.

[0024] It should be understood that both the foregoing general description and the following detailed description are exemplary and are intended to provide further explanation of the subject technology claimed. BRIEF DESCRIPTION OF DRAWINGS

[0025] The above and other objects, features and advantages of the present disclosure will become more apparent from the following detailed description when taken in conjunction with the accompanying drawings in which: The accompanying drawings are provided to assist in understanding the embodiments of the present disclosure, and constitute a part of the specification. The accompanying drawings together with the specification serve to explain the present disclosure, and do not constitute a limitation of the present disclosure. In the drawings, the same reference numerals generally refer to the same components or steps throughout the drawings.

[0026] Figure 1 A structural schematic view of an optical test structure for a turbine blade cold effect test of an aero-engine provided by an embodiment of the present disclosure;

[0027] Figure 2 A structural schematic view of an optical test structure for a turbine blade cold effect test of an aero-engine provided by an embodiment of the present disclosure; Figure 1 A sectional view along A-A in FIG. 4;

[0028] Figure 3 A structural schematic view of an optical test structure for a turbine blade cold effect test of an aero-engine provided by an embodiment of the present disclosure;

[0029] Figure 4 A structural schematic view of an optical test structure for a turbine blade cold effect test of an aero-engine provided by an embodiment of the present disclosure.

[0030] 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 pipe; 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 transmission device; 9, protective cover; 100, light source; 200, blade; 300, combustion chamber. DETAILED DESCRIPTION

[0031] In order to make the objectives, technical solutions and advantages of the present disclosure more apparent, the following will describe the example embodiments according to the present disclosure in detail 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, and it should be understood that the present disclosure is not limited by the example embodiments described herein.

[0032] The term "include" and variations thereof, as used in this document, is used expansively and means "including, but not limited to". The term "based on" is not limited to a built-in or hard-wired response and can be implemented at least in part using operations, logic, and / or other implementations appropriate to an implementation. The term "one embodiment" is used herein to refer to at least one embodiment. The term "another embodiment" is used herein to refer to at least one additional embodiment. The term "some embodiments" is used herein to refer to at least one embodiment. Relative terms such as "first", "second", and the like can be used solely to distinguish one entity or action from another, without necessarily giving any sense of sequence or order or importance. Other terms can be defined by their context.

[0033] It should be noted that the modification of "one", "multiple" mentioned in the present disclosure is illustrative and not restrictive, and those skilled in the art should understand that unless the context clearly indicates otherwise, it should be understood as "one or more".

[0034] Since the turbine blade is an important hot end power output component of the aero-engine, it works in a high temperature and high pressure environment for a long time, which is easy to cause damage and failure, thereby threatening the normal operation of the engine. Therefore, the turbine blade needs to be tested to measure its temperature distribution and the like in the working state, so as to ensure its stability and durability under extreme working conditions, thereby ensuring the overall reliability and safety of the engine.

[0035] Specifically, the turbine blade can be tested by optical testing methods such as infrared or fluorescence. However, the high temperature and high pressure operating environment of the aero-engine turbine blade cooling effect test can cause high intensity heat conduction to the optical path, resulting in optical test noise in the optical path. The optical test noise can weaken or mask the infrared or fluorescence optical characteristics of the target blade, thereby affecting the accuracy of the blade cooling effect test results.

[0036] Based on this, the embodiment of the present disclosure provides an optical testing structure for aero-engine turbine blade cooling effect test to improve the accuracy of the blade cooling effect test results. The optical testing structure for aero-engine turbine blade cooling effect test provided by the present disclosure will be described in detail below with reference to the specific embodiments and the accompanying drawings:

[0037] Referring to Figures 1 to 4 The embodiment of the present disclosure provides an optical testing structure for aero-engine turbine blade cooling effect test, which is specifically used for cooling effect test of the engine turbine blade.

[0038] The aero-engine specifically includes a compressor, a combustion chamber 300, a turbine, and a tail nozzle. The compressor is used to compress air. The compressed air is mixed with fuel in the combustion chamber 300 and burned to produce high temperature and high pressure gas. The high temperature and high pressure gas drives the turbine blade 200 to rotate, so that the gas is ejected through the tail nozzle to provide thrust for the aircraft flight.

[0039] The optical testing structure for the turbine blade cold effect test of the aero-engine provided by the embodiments of the present disclosure comprises optical glass 1 and an optical channel tube 4.

[0040] The optical glass 1 is located at the light-in side of the optical channel tube 4, and the light-in side of the optical channel tube 4 is provided with an optical glass base 2, the optical glass 1 is arranged on the optical glass base 2, and the light-out side of the optical channel tube 4 faces the target blade 200.

[0041] Referring to Figure 4 shown, in specific implementation, the test light source 100 is placed at the light-in side of the optical glass 1, and the light source 100 can be an infrared light source or a fluorescent light source, and the embodiments of the present disclosure are not limited thereto, as long as the test light source can be provided. The light emitted by the light source 100 enters from the light-in side of the optical glass 1 and exits from the light-out side of the optical glass 1, enters into the optical channel tube 4, the inner cavity of the optical channel tube 4 forms an optical path, and 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, and by analyzing these parameters, the stability and durability of the blade 200 under extreme working conditions can be ensured, thereby ensuring the overall reliability and safety of the engine.

[0042] The optical testing structure for the turbine blade cold effect test of the aero-engine further comprises an outer casing 3 and a film ring 5. The outer casing 3 is sleeved on the outside of the optical channel tube 4, a cooling channel 31 for the cooling medium to flow is formed between the inner wall of the outer casing 3 and the outer wall of the optical channel tube 4, and the outer casing 3 is provided with a cooling medium inlet 311 and a cooling medium outlet 312 which respectively communicate with the cooling channel 31, so as to cool the optical channel tube 4.

[0043] In specific implementation, the cooling medium inlet 311 can be communicated with an external cooling medium supply container, so as to provide the cooling medium for the cooling channel 31 through the cooling medium supply container. The cooling medium enters into 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 wall of the optical channel tube 4, and the cooling medium which absorbs the heat finally flows out from the cooling medium outlet 312, as shown in Figure 3 shown, the flow direction of the cooling medium can be the direction indicated by the solid arrow shown in Figure 3 so as to cool the optical channel tube 4, and further cool and lower the temperature of the inner cavity of the optical channel tube 4, so as to 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 the optical testing noise in the optical path of the inner cavity of the optical channel tube 4.

[0044] For example, the above-mentioned cooling medium can be cooling water.

[0045] Of course, in other implementations, the cooling medium can also be other cooling liquids, such as liquid metal, oil-water mixtures, or emulsion coolants. Alternatively, it can be a cooling gas, as long as it can flow within the cooling channel 31 to cool the optical channel tube 4.

[0046] The gas film ring 5 is sealed 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-exiting side of the optical glass 1. Specifically, the optical glass base 2 is provided with a cooling gas inlet 21, and the gas film ring 5 has gas jet holes that communicate with the cooling gas inlet 21 and the inner cavity of the optical channel tube 4, respectively, so that the cooling gas can perform jet sweeping on the light-exiting surface of the optical glass 1, and allow the cooling gas to enter into the optical channel tube 4 to cool the optical channel tube 4.

[0047] For example, the optical glass base 2 can be annular, and it is coaxially arranged with the optical channel tube 4. It is understood that the inner diameter of the optical glass base 2 is not less than the inner diameter of the optical channel tube 4 to ensure normal light transmission. Of course, in other implementations, the optical glass base 2 may not be annular, as long as it effectively supports the optical glass 1 and its axial projection is located outside the axial projection of the optical channel tube 4, thus not obstructing light.

[0048] Similarly, the axial projection of the air film ring 5 is located outside the axial projection of the optical channel tube 4, which does not block the light and ensures effective light transmission.

[0049] In a practical implementation, the cooling gas inlet 21 can be connected to an air-cooling pipe, through which cooling gas is introduced into the cooling gas inlet 21. For example, the cooling gas inlet 21 can be installed together with the air-cooling pipe via a threaded connection. For instance, the optical glass base 2 is provided with a channel communicating with the cooling gas inlet 21. The channel inlet is connected to the cooling gas inlet 21, and the channel outlet is connected to the gas jet hole of the gas film ring 5. The cooling gas entering through the cooling gas inlet 21 is ejected through the gas jet hole 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 direction of the cooling gas flow can be, for example, Figure 3 The direction indicated by the dashed arrow shown.

[0050] Furthermore, 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 hole 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 passage of the engine accidentally fly into the optical channel tube 4, the cooling gas can sweep the light-emitting surface of the optical glass 1 to clean the optical glass 1, prevent particulate matter from contaminating the optical glass 1, protect the optical glass 1, and improve the accuracy of the test.

[0051] Since the cooling medium introduced into the inner cavity of the optical channel tube 4 is gas, compared with the scheme of introducing cooling liquid into the inner cavity of the optical channel tube 4, the cooling gas will not affect the optical path. In specific implementation, the cooling gas can be air, or gases of different temperature levels and different compositions.

[0052] For example, the optical glass base 2 can be provided with one cooling gas inlet 21 or multiple cooling gas inlets 21. For example, multiple cooling gas inlets 21 can be arranged at intervals along the circumference of the optical glass 1, so that cooling gas can be introduced from multiple positions in the circumference at the same time, thereby improving the cooling effect and cooling efficiency.

[0053] In practice, the pressure and flow rate of the cooling gas and cooling medium can be adjusted according to actual needs, or they can be supplied at a constant pressure. For example, a controller can be set up to adjust the pressure and flow rate of the cooling gas and cooling medium.

[0054] The cooling gas and cooling medium can be recycled, reducing testing costs.

[0055] The optical test structure for testing the cooling effect of turbine blades in this embodiment of the present disclosure comprises an optical glass 1, an outer casing 3, and an optical channel tube 4. The outer casing 3 is fitted over the outer side of 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 through 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 supporting the optical glass 1 is provided on the light-incident side of the optical channel tube 4, and a cooling gas inlet 21 is provided on the optical glass base 2. A gas film ring 5 is sealed between the optical glass base 2 and the light-incident side of the optical channel tube 4, allowing the cooling gas to pass through the optical glass 1 sequentially. The cooling gas inlet 21 on the glass base 2 and the gas jet hole on the gas film ring 5 enter the optical channel tube 4 to cool the inner cavity of the optical channel tube 4, thereby reducing the temperature inside the optical channel tube 4. In other words, the cooling channel 31 on the outside of the optical channel tube 4 and the cooling gas entering the inner cavity of the optical channel tube 4 work together to cool the inner cavity of the optical channel tube 4, achieving dual cooling and temperature reduction of the inner cavity of the optical channel tube 4. This provides a continuous cooling operating environment for the inner cavity of the optical channel tube 4, thereby weakening the optical test noise caused by the heat conduction of the optical path due to the high temperature and high pressure operating environment to a certain extent. This also avoids the interference of optical noise on the optical characteristics of the target blade to a certain extent, improves the accuracy of the blade cooling effect test results, and provides accurate and effective data support for engine test research.

[0056] Meanwhile, since the gas film ring 5 is sealed 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-outceasing side of the optical glass 1, the cooling gas entering from the cooling gas inlet 21 of the optical glass base 2 can sweep the light-outceasing surface of the optical glass 1 after being ejected through the gas jet hole on the gas film ring 5. This, to a certain extent, avoids the situation where tiny carbide particles in the high-speed combustion gas in the main combustion passage of the engine fly into the inner cavity of the optical channel tube 4 and contaminate the optical glass 1, thereby improving the cleanliness of the optical glass 1 and ensuring the accuracy of the test results.

[0057] In practice, a heat-resistant anti-reflective coating can be set on the light-incident surface of the optical glass 1, thereby improving the light transmission ability and thus improving the accuracy of the test results.

[0058] Continue to refer to Figure 2 and Figure 3 As shown, in some embodiments, the cooling channel 31 is provided with a spiral rib 313 extending spirally along the axial direction of the optical channel tube 4, so that the cooling channel 31 is formed as a spiral cooling channel 31 for the flow of cooling medium.

[0059] This configuration extends the flow path 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 effect of the optical channel tube 4, and further improving the test efficiency and accuracy.

[0060] In some embodiments, the spiral rib 313 can be integrally formed with the outer casing 3. This improves the overall structural strength of the spiral rib 313 and the outer casing 3 to a certain extent.

[0061] In other implementations, the spiral rib 313 can be integrally formed with the optical channel tube 4, or the optical channel tube 4, the spiral rib 313, and the outer casing 3 can be integrally formed.

[0062] Combination Figures 1 to 3 As shown, in some embodiments, the cooling medium inlet 311 is located near the light-incident side of the optical channel tube 4, and the cooling medium outlet 312 is located near the light-outcident side of the optical channel tube 4.

[0063] This increases the contact area between the cooling medium and the wall of the optical channel tube 4, thereby improving the cooling efficiency and effect of the optical channel tube 4. Moreover, this also avoids the situation where the cooling medium flowing in from the cooling medium inlet 311 is discharged directly from the cooling medium outlet 312 before it has fully exchanged heat with the wall of the optical channel tube 4, further improving the cooling efficiency and effect.

[0064] 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 in communication with the inner cavity of the optical channel tube 4.

[0065] This allows the cooling gas entering through the cooling gas inlet 21 to be buffered in the gas supply and pressure stabilization chamber 51, thereby further ensuring the stability of the pressure and cooling gas flow within the optical channel tube 4, and further guaranteeing the accuracy of the test results.

[0066] Continue to refer to Figures 1 to 4 As shown, in some embodiments, the optical testing structure for the cold effect test of aero-engine turbine blades provided in this disclosure further includes an annular optical glass clamping member 6. The optical glass clamping member 6 is located on the side of the optical glass 1 facing away from the optical glass base 2, to press the optical glass 1 onto the optical glass base 2.

[0067] By setting the optical glass clamping component 6, the stability of the optical glass 1 is further improved, thereby further ensuring the stability of the optical transmission path and thus improving the accuracy of the test results.

[0068] It is understandable that the axial projection of the optical glass clamping member 6 is located outside the axial projection of the optical channel tube 4, so that the optical glass clamping member 6 will not interfere with the normal transmission of light.

[0069] In some embodiments, the optical glass clamping member 6 and the optical glass base 2 can be detachably connected.

[0070] Reference Figure 2 As shown, for example, both the optical glass clamping component 6 and the optical glass base 2 are provided with mounting holes. The optical glass clamping component 6 and the optical glass base 2 are connected together by fasteners 61 that pass through the corresponding mounting holes. The fasteners 61 can be, for example, fastening bolts.

[0071] For example, the optical glass clamping component 6 and the optical glass base 2 can also be detachably connected together by means of elastic buckles and snap holes.

[0072] This design allows for easy replacement or repair of the optical glass 1 by simply detaching the optical glass clamping component 6 and the optical glass base 2 when needed. Furthermore, if either the optical glass clamping component 6 or the optical glass base 2 is damaged, detaching both components allows for replacement of only the damaged part, preventing the entire structure from being scrapped and saving costs.

[0073] Combination 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 clamping member 6, and a second positioning groove 62 is provided on the side of the optical glass clamping member 6 facing the optical glass base 2. The first positioning groove 22 and the second positioning groove 62 together define a positioning groove, and the optical glass 1 is located in the positioning groove.

[0074] This setup ensures reliable positioning of the optical glass 1, further improving its stability and guaranteeing a smooth experimental process, thus enhancing the accuracy of the test results.

[0075] In some embodiments, a flexible graphite ring 7 is provided between the optical glass clamping member 6 and the optical glass 1, and the flexible graphite ring 7 is arranged circumferentially along the outer edge of the optical glass 1. Alternatively, a flexible graphite ring 7 can be provided between the optical glass 1 and the optical glass base 2, and the flexible graphite ring 7 is arranged circumferentially along the outer edge of the optical glass 1.

[0076] It is understandable that the flexible graphite ring 7 is set 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 will not block the light and ensure the normal and effective transmission of the light.

[0077] By setting up a 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.

[0078] In some embodiments, the optical test structure for testing the cold effect of aero-engine turbine blades also includes a protective cover 9, which is detachably disposed on the light-incident side of the optical glass 1.

[0079] When the test is completed or not conducted, the protective cover 9 is placed on the light-incident side of the optical glass 1 to effectively protect the optical glass 1 and prevent it from being contaminated or damaged. This ensures accurate testing and facilitates the handling or movement of the optical test structure for the cold effect test of the blade.

[0080] In a specific implementation, for example, the optical glass clamping member 6 is annular, and the protective cover 9 has a protrusion on the side facing the optical glass 1. This protrusion matches the annular inner cavity of the optical glass clamping member 6. When the protective cover 9 is placed on the light-incident side of the optical glass 1, the protrusion extends into the annular inner cavity of the optical glass clamping member 6 to achieve matching and covering.

[0081] For example, the protective cover 9 includes a cover body and an annular rim provided around the circumference of the cover body. The cover body covers the light-incident side of the optical glass 1, and the annular rim surrounds the outer side of the optical glass base 2.

[0082] Continue to refer to Figure 2 As shown, in some embodiments, an optical fiber transmission device 8 may also be provided on the light-incident side of the optical glass 1.

[0083] By setting the optical fiber transmission device 8, the stability and reliability of light input are further improved, and the applicability of the optical test structure for testing the cold effect of aero-engine turbine blades provided in this embodiment is further expanded.

[0084] In specific tests, for example, the main gas parameters are: pressure 1.5 MPa, flow rate 6.8 kg / s, and temperature 1600 K. The optical test structure for the cold effect test of aero-engine turbine blades provided in this disclosure can keep the optical path stable at room temperature, greatly reducing optical noise, preventing the generation of optical signals that obstruct or interfere with the optical characteristics of the target blade, and preventing the phenomenon of small carbonized particles of the main gas contaminating the optical lens, ensuring stable and reliable operation.

[0085] The optical testing structure for the cooling effect test of aero-engine turbine blades provided in this disclosure provides structural support for optical testing (such as infrared optics, excited fluorescence, etc.) of the wall temperature field of characteristic parts such as the leading edge, trailing edge, blade base, and blade back in the equivalent whole-engine high-temperature and high-pressure cooling effect test of aero-engine turbine blades. It can also be used for wall deposition recording or macroscopic crack development recording in molten sand and dust erosion tests or thermal shock / fatigue tests of aero-engine hot-end components, providing support for comparative analysis of deposition performance and deposition phenomena of the test object or for thermal intensity analysis of the test object.

[0086] The optical testing structure for the cold effect test of aero-engine turbine blades provided in this disclosure can broaden the application scope of optical temperature measurement schemes for engineering iterative design and experimental research verification. It reduces the strong optical testing noise caused by intense heat conduction and radiation under near-realistic operating conditions, and reduces or completely avoids the probability of weakening or obscuring the infrared or fluorescence characteristics of the test target due to the contamination of the inner wall of the transparent glass on the optical channel by tiny carbonized particles. It can also reduce interference caused by unintended heat conduction in basic theoretical research in universities, improve the ability to discern the influence of boundary condition parameters on the research target parameters and the analysis of influence weights, and greatly shorten the on-site preparation time for experimental research or verification, thereby improving experimental efficiency.

[0087] The above description is merely an illustration of some embodiments of this disclosure and the technical principles employed. Those skilled in the art should understand that the scope of this disclosure is not limited to technical solutions formed by specific combinations of the above-described technical features, but should also cover other technical solutions formed by arbitrary combinations of the above-described technical features or their equivalents without departing from the above-described concept. For example, technical solutions formed by substituting the above features with (but not limited to) technical features disclosed in this disclosure that have similar functions.

[0088] While specific embodiments of this disclosure have been described in detail by way of example, those skilled in the art should understand that the examples are for illustrative purposes only and not intended to limit the scope of this disclosure. Those skilled in the art should understand that modifications can be made to the above embodiments without departing from the scope and spirit of this disclosure. The scope of this disclosure is defined by the appended claims.

Claims

1. An optical testing structure for testing the cooling effect of aero-engine turbine blades, characterized in that, Includes optical glass, outer casing, and optical channel tube; The optical glass is located on the light-incident side of the optical channel tube, and 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, and the light-exit side of the optical channel tube faces the target blade. The outer casing is fitted over the outside of the optical channel tube. A cooling channel for the flow of cooling medium is formed between the inner wall of the outer casing and the outer wall of the optical channel tube. The outer casing has a cooling medium inlet and a cooling medium outlet that are respectively connected to the cooling channel to cool the optical channel tube. A gas film ring is sealed 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-outceasing side of the optical glass. A cooling gas inlet is provided on the optical glass base, and the gas film ring has gas jet holes that communicate with the cooling gas inlet and the inner cavity of the optical channel tube, respectively, so that the cooling gas can perform jet sweeping on the light-outceasing surface of the optical glass and enter the optical channel tube to cool the optical channel tube.

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

3. The optical testing structure for testing the cold effect of aero-engine turbine blades according to claim 2, characterized in that, The spiral ribs are integrally formed with the outer casing.

4. The optical testing structure for testing the cold effect of aero-engine turbine blades according to claim 1, characterized in that, The cooling medium inlet is located near the light-incident side of the optical channel tube; The cooling medium outlet is located near the light-emitting side of the optical channel tube.

5. The optical testing structure for testing the cold effect of aero-engine turbine blades according to claim 1, characterized in that, An air supply and pressure stabilization cavity is defined between the air film ring and the optical glass base, and the air supply and pressure stabilization cavity is connected to the inner cavity of the optical channel tube.

6. The optical testing structure for testing the cold effect of aero-engine turbine blades according to claim 1, characterized in that, It also includes annular optical glass clamping components; The optical glass clamping member is located on the side of the optical glass opposite to the optical glass base, so as to press the optical glass onto the optical glass base.

7. The optical testing structure for testing the cold effect of aero-engine turbine blades according to claim 6, characterized in that, The optical glass clamping component is detachably connected to the optical glass base; And / or, the optical glass base has a first positioning groove on the side facing the optical glass clamping member, and the optical glass clamping member has a second positioning groove on the side facing the optical glass base. The first positioning groove and the second positioning groove together define a positioning groove, and the optical glass is located in the positioning groove.

8. The optical testing structure for testing the cold effect of aero-engine turbine blades according to claim 6, characterized in that, A flexible graphite ring is provided between the optical glass clamping 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 provided between the optical glass and the optical glass base, the flexible graphite ring being arranged circumferentially along the outer edge of the optical glass.

9. The optical testing structure for testing the cold effect of aero-engine turbine blades according to any one of claims 1 to 8, characterized in that, The optical glass is also provided with an optical fiber transmission device on the light-incident side.

10. The optical testing structure for testing the cold effect of aero-engine turbine blades according to any one of claims 1 to 8, characterized in that, It also includes a protective cover, which is detachably disposed on the light-incident side of the optical glass.

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