An apparatus and system for testing a high-pressure turbine rotor of an aeroengine

Abstract

The present disclosure relates to an apparatus and a system for testing a high-pressure turbine rotor of an aeroengine. The apparatus includes an apparatus for providing signal transmission, comprising: a rotor member provided with one or more rotating conductive devices thereon; a stator member including one or more conductive devices, wherein one or more conductive devices on the stator member are conductively contacted with one or more rotating conductive devices on the rotor member; and a transfer shaft including a first section and a second section, wherein the rotor member is coupled between the second section of the transfer shaft and the stator member, and wherein one or more holes are provided on the first section of the transfer shaft to form a passage passing through the one or more holes on the first section. The apparatus of the present disclosure is connected to the rear end of the high-pressure turbine rotor, and holes are opened on the first section of the transfer shaft to keep the seal air path of the high-pressure turbine rear bearing cavity coherent, thereby ensuring the sealing of the high-pressure turbine rear bearing cavity.

Description

Technical Field

[0001] The present disclosure relates to the field of aeroengines, and particularly relates to an apparatus and a system for testing a high-pressure turbine rotor of an aeroengine. Background Art

[0002] Accurately measuring and acquiring the surface temperature and strain of key structural components of an aeroengine in-situ are crucial for improving the working efficiency of the aeroengine, enhancing the reliability of the aeroengine, reducing pollution emissions, designing new aeroengines, and achieving successful engine tests.

[0003] When an aeroengine is being tested, sensing parts (such as temperature sensing parts and strain sensing parts, etc.) need to be installed on the surface of the rotor blades of the aeroengine and rotate at high speed with the rotor. This may make it difficult to transmit the measurement signals from the sensing parts to ground equipment for processing, analysis, storage, etc. At the same time, it is also challenging to provide power excitation for the sensing parts that rotate at high speed with the rotor during the engine test process.

[0004] Therefore, for measurement signals in a rotating state, there is an urgent need for a measurement device that can efficiently and reliably transmit the measurement signals to ground equipment. Summary of the Invention

[0005] The following presents a brief overview of one or more aspects to provide a basic understanding of such aspects. This overview is not an exhaustive survey of all contemplated aspects, and is neither intended to identify key or critical elements of all aspects nor to define the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form as a prelude to the more detailed description that follows.

[0006] The purpose of the present disclosure is to provide an apparatus and a system for testing a high-pressure turbine rotor of an aeroengine.

[0007] In one aspect, an apparatus for providing signal transmission may include:

[0008] A rotor member having one or more rotating conductive devices provided thereon;

[0009] A stator member including one or more conductive devices, wherein the one or more conductive devices on the stator member are conductively contacted with the one or more rotating conductive devices on the rotor member; and

[0010] A transfer shaft including a first section and a second section, wherein the rotor member is coupled between the second section of the transfer shaft and the stator member, and wherein one or more holes are provided on the first section of the transfer shaft to form a passage passing through the one or more holes on the first section.

[0011] In one example, the one or more holes on the first section of the transfer shaft include: multiple rows of holes arranged uniformly or non-uniformly on the first section.

[0012] In another example, a device for providing signal transmission may further include:

[0013] A stator support member that surrounds the stator member;

[0014] A cooling sandwich layer, one end of which is connected to the stator support member; and

[0015] A cooling pipeline, wherein the cooling pipeline is led to a rotating conductive device on the rotor member through the stator member.

[0016] In yet another example, the rotating conductive device on the rotor member is connected to a first lead segment of a lead wire, and the conductive device on the stator member is connected to a second lead segment of the lead wire, wherein the rotating conductive device on the rotor member and the corresponding conductive device on the stator member transmit signals between the first lead segment and the second lead segment.

[0017] In one aspect, a test system for testing a high-pressure turbine rotor of an aeroengine may include:

[0018] A device for providing signal transmission as described in the above aspects, the device being connected to the high-pressure turbine rotor, wherein:

[0019] The first section of the transfer shaft is connected to the rear shaft of the high-pressure turbine,

[0020] The rotor member is mechanically coupled to the second section of the transfer shaft through a coupling to rotate together with the transfer shaft and the high-pressure turbine rotor, and

[0021] The device for providing signal transmission is fixed on the aeroengine.

[0022] In one example, a test system for testing a high-pressure turbine rotor of an aeroengine may further include:

[0023] One or more sensing parts pasted on the high-pressure turbine rotor, wherein the one or more sensing parts are connected to one or more rotating conductive devices on the rotor member through a first lead segment of a lead wire.

[0024] In another example, after the second lead segment of the lead wire is led out from one or more conductive devices of the stator part of the device, it passes through the center of the rotating shaft and exits from the outlet of the high-pressure test tail nozzle center cone through the high-pressure test tail nozzle center cone. The lead wire includes a lead wire for obtaining signals from the sensing part and a lead wire for providing power excitation to the sensing part.

[0025] In yet another example, the passage passing through one or more holes on the first segment extends through the holes on the bearing housing and the holes on the inter-stage casing to the outlet of the high-pressure test tail nozzle center cone.

[0026] In still another example, the device for providing signal transmission fixed on the aeroengine further includes:

[0027] The stator support of the stator part of the device is fixed on the rear seal on the inner side of the inter-stage casing; and

[0028] One side of the cooling sandwich of the device is fixed on the stator support, and the other side of the cooling sandwich overlaps on the inner wall of the high-pressure test tail nozzle center cone.

[0029] In yet another example, the cold air led to the rotating conductive device on the rotor part by the cooling pipeline flows out from the cooling sandwich.

[0030] The test device according to an embodiment of the present disclosure can be connected to the rear end (for example, the rear shaft of the high-pressure turbine) of the high-pressure turbine rotor of the aeroengine. In this embodiment, holes can be opened on the first segment of the adapter shaft to keep the sealing air path of the high-pressure turbine rear bearing cavity coherent, so as to ensure the sealing of the high-pressure turbine rear bearing cavity. In a preferred embodiment, the test device can further include a stator support, which surrounds the stator part of the test device and is fixed on the rear seal on the inner side of the inter-stage casing of the aeroengine. The stator support is tightly connected to the rear seal to prevent the air path from flowing out therefrom, so as to ensure that the sealing air path of the high-pressure turbine rear bearing cavity remains coherent along the established path trajectory, thereby ensuring the sealing of the high-pressure turbine rear bearing cavity.

[0031] In a preferred embodiment of the present disclosure, the lead wires and cooling pipelines introduced or led out from the stator part pass through the high-pressure test tail nozzle center cone along the center of the rotating shaft and exit from the outlet of the high-pressure test tail nozzle center cone, and are connected to the test bench and ground equipment with the shortest length. Preferably, the stator part can further include a cooling sandwich, one end of which is fixed on the stator support, and the other end overlaps on the inner wall of the high-pressure test tail nozzle center cone. Preferably, the cold air introduced from the cooling pipeline does not flow out of the cooling pipeline, but flows out from the cooling sandwich, thereby reducing the pipeline led out from the outlet of the high-pressure test tail nozzle center cone along the center of the rotating shaft through the high-pressure test tail nozzle center cone.

[0032] Compared with the connection method of coupling the test equipment to the front end of the high-pressure turbine rotor, the connection method of coupling the test equipment to the rear end of the high-pressure turbine rotor can greatly shorten the lengths of leads, cooling pipelines, etc. In this way, the leads and pipelines are not easily damaged during rotation, and their service lives are significantly extended, thus ensuring the accuracy, reliability, and stability of signal measurement. In addition, when there is no need to measure the aeroengine, only the rear shaft of the high-pressure turbine, the rear seal, and the high-pressure test tail spray center cone need to be replaced. The replacement is convenient and easy to operate.

[0033] The present invention content is provided to introduce some concepts in a simplified form, and these concepts will be further described in the following detailed implementation manners. The present invention content is not intended to identify the key features or essential features of the claimed subject matter, nor is it intended to be used to limit the scope of the claimed subject matter. Other aspects, features, and / or advantages of the various embodiments will be partly described below, and will be partly obvious from the description, or can be learned through the practice of the present invention. Brief Description of the Drawings

[0034] In order to understand the manner in which the above-described features of the present disclosure can be used, a more specific description of the above briefly summarized content can be made by referring to the various aspects, some of which are illustrated in the drawings. However, it should be noted that the drawings only illustrate some typical aspects of the present disclosure, and thus should not be considered to limit its scope, because the description may allow other equally effective aspects. In the drawings:

[0035] Figure 1 A schematic structural diagram of an aeroengine is shown;

[0036] Figure 2 A schematic structural diagram of a device for providing signal transmission according to an embodiment of the present disclosure is shown;

[0037] Figure 3 It is an assembly schematic diagram for connecting a device for providing signal transmission to the high-pressure turbine rotor of an aeroengine according to an embodiment of the present disclosure;

[0038] Figure 4a A cross-sectional view of the adapter shaft of a device for providing signal transmission according to an embodiment of the present disclosure is shown;

[0039] Figure 4b A schematic diagram of the hole distribution on the first section of the adapter shaft viewed from the left side of the adapter shaft according to an embodiment of the present disclosure is shown;

[0040] Figure 5 A schematic diagram of a rotor member coupled to the second section of the adapter shaft through a coupling according to an embodiment of the present disclosure is shown;

[0041] Figure 6a A cross-sectional view of a part of a device for providing signal transmission according to an embodiment of the present disclosure is shown;

[0042] Figure 6b A contour diagram of a part of a device for providing signal transmission according to an embodiment of the present disclosure is shown;

[0043] Figure 7 A schematic diagram of the flow path of cold air flowing out of the cooling sandwich layer of a device for providing signal transmission according to an embodiment of the present disclosure is shown; and

[0044] Figure 8 A schematic diagram of the connection between the stator support of a device for providing signal transmission and the engine according to an embodiment of the present disclosure is shown.

[0045] The reference signs in the drawings are:

[0046] Fan 1, booster stage 2, intermediate casing 3, high-pressure compressor 4, combustion chamber 5, high-pressure turbine 6, inter-stage casing 7, low-pressure turbine 8, low-pressure turbine rear casing 9, high-pressure turbine rotor speed sensor 10, aero-engine core engine test piece 11;

[0047] A device 200 for providing signal transmission, adapter shaft 201 (the first section 2011 and the second section 2012 of the adapter shaft), rotor member 202, stator member 203, one or more holes 204, stator support 205, cooling sandwich layer 206, lead wire 207, cooling pipeline 208; and

[0048] Bearing housing 302, inter-stage casing 303, low-pressure turbine rear casing 304, mounting edge 305 of the high-pressure test tail nozzle center cone, outlet 306 of the high-pressure test tail nozzle center cone. Detailed Description of the Embodiment

[0049] The following detailed description presented in conjunction with the accompanying drawings is intended as a description of various configurations and is not intended to represent the only configurations in which the concepts described herein can be practiced. This detailed description includes specific details to provide a thorough understanding of the various concepts. However, it will be apparent to those skilled in the art that these concepts can be practiced without these specific details.

[0050] Based on this teaching, those skilled in the art should appreciate that the scope of the present invention is intended to cover any aspect of the present invention, whether implemented independently or in combination with any other aspect of the present invention. For example, any number of the aspects described can be used to implement a device or practice a system. Additionally, the scope of the present invention is intended to cover such devices or systems practiced using other structures, functions, or structures and functions that are complementary to or different from the various aspects of the present invention described.

[0051] Although specific aspects are described herein, numerous variations and permutations of these aspects fall within the scope of the present invention. While some benefits and advantages of the preferred aspects are mentioned, the scope of the present invention is not intended to be limited to specific benefits, uses, or objectives. The detailed description and the drawings merely illustrate the present invention and do not limit the present invention, and the scope of the present invention is defined by the appended claims and their equivalent technical solutions.

[0052] When an aeroengine is being tested, sensing parts (such as temperature sensing parts and strain sensing parts, etc.) need to be installed on the surface of the rotor blades of the aeroengine and rotate with the rotor, which may make it difficult to transmit the measurement signals from the sensing parts to the load safety test system, the test bench, and the ground equipment for processing, analysis, storage, etc. At the same time, during the test run, it is also challenging to provide power excitation for the sensing parts that rotate with the rotor.

[0053] However, the strain and temperature of the high-pressure turbine rotor blades belong to airworthiness subjects, and aeroengine manufacturers must provide relevant test data on the dynamic stress of the high-pressure turbine rotor under various working conditions. The test data meet the margin conditions, that is, the high-pressure turbine rotor blades meet the relevant standards, and the probability of damage, rupture, etc. during flight is greatly reduced. Therefore, it is essential to test the high-pressure turbine rotor under various working conditions (especially during the test run).

[0054] To solve one or more of the technical problems existing in the prior art, one aspect of the present disclosure proposes a test system for testing the high-pressure turbine rotor of an aeroengine. The test system may include a device for providing signal transmission and one or more sensing parts. The device for providing signal transmission may include a transfer shaft, a rotor part, and a stator part, wherein one or more rotating conductive devices may be provided on the rotor part, and the stator part may include one or more conductive devices. Preferably, the stator part may optionally include a stator support. More preferably, the stator part may optionally include a cooling sandwich. Additionally, the test system may optionally include ground equipment, such as but not limited to the acquisition system of the test bench or other ground acquisition systems, etc.

[0055] Generally, the sensing parts may be pasted on the blades of the high-pressure turbine rotor and connected to one or more rotating conductive devices of the rotor part through the first lead segment of the lead wire, and the one or more rotating conductive devices are conductively contacted with the one or more conductive devices of the stator part, and the second lead segment of the lead wire is led out from the one or more conductive devices of the stator part.

[0056] The device for providing signal transmission is an electrical component responsible for connecting and transmitting power and signals to the rotating body. Although the structure of the device for providing signal transmission is not specifically shown in the accompanying drawings of the specification, those skilled in the art will understand that the device for providing signal transmission is usually installed at the rotation center of the device under test and consists of a rotating part, a stationary part, and an accessory part. The rotating part is connected to the rotating structure to be tested and rotates therewith, and is called the "rotor", while the stationary part is connected to the fixed structure of the device and is called the "stator".

[0057] For example, the device for providing signal transmission can be a slip ring. A slip ring, also known as a rotary electrical interface or electrical rotary joint, can be used in scenarios where there is an unlimited continuous rotation and at the same time power or data needs to be transmitted from a rotating position to a fixed position. The slip ring as a whole relies on the elastic lapping principle, the rolling lapping principle, or the sealing principle, as well as the ingenious design of the motion structure and the sealing structure, precise manufacturing and fitting of parts, reasonable material selection, etc., to form a stable and reliable rotating connection system. For example, a slip ring can use the sliding or rolling contact of conductive components, electrostatic coupling, or electromagnetic coupling to transmit electrical signals and electrical energy between the rotating component and the stationary component. There are drive elements, measurement elements, and control elements on the rotating component, and control signals and power supplies must be supplied to them. This requires various slip ring assemblies to transmit signals and energy. The number of lines that need to be rotationally connected can be more than a hundred. First of all, in the structural design, it is necessary to ensure reliable contact and ensure that all lines are continuously connected.

[0058] As long as the rotating body of the slip ring is attached to an infinitely rotating device, power energy can be provided to the rotating body, enabling the rotating body to complete detection, testing, etc. while performing infinite rotational motion. A slip ring can collect up to 150 measurement points (for example, 300 connected lines), while ensuring that the signals are clearly transmitted to the ground device without interference. According to the transmission medium, the device for providing signal transmission can be divided into electrical slip rings, fluid slip rings, optical slip rings, etc. It should be noted that although electrical slip rings are used as examples in this disclosure for description, any type of device for providing signal transmission that can transmit signals from the rotor part to the stator part is applicable to this disclosure.

[0059] In the test system described according to one aspect of the present disclosure, the device for providing signal transmission is designed to be installed at the rear end of the high-pressure turbine rotor. The measurement signals from the sensors on the high-pressure turbine rotor can be transmitted to the ground equipment through the first lead segment of the lead wire, the rotating conductive device of the rotor part, the conductive device of the stator part, the second lead segment of the lead wire, etc. After the second lead segment of the lead wire is led out from the stator part, it passes through the center of the rotating shaft, passes through the high-pressure test tailpipe center cone from the outlet of the high-pressure test tailpipe center cone, and is connected to the ground equipment, etc. Thus, the total length of the lead wire from one or more sensors to the ground equipment is much shorter than that in the case where the device for providing signal transmission is installed at the front end of the high-pressure turbine rotor, thereby ensuring the service life of the test system and ensuring the stability, accuracy, and reliability of the test signals.

[0060] In addition, in the device for providing signal transmission described in the present disclosure, one or more holes can be provided on the first segment of the adapter shaft to form a passage extending through the one or more holes on the first segment and connecting to the original sealing air path of the high-pressure turbine rear bearing cavity, thereby ensuring the sealing of the high-pressure turbine rear bearing cavity. The following will be specifically described in conjunction with the drawings.

[0061] As an example, Figure 1 shows a schematic structural diagram of an aeroengine. As Figure 1 shown, the aeroengine can include: a fan 1, a booster stage 2, an intermediate casing 3, a high-pressure compressor 4, a combustion chamber 5, a high-pressure turbine 6, an inter-stage casing 7, a low-pressure turbine 8, a low-pressure turbine rear casing 9, and a high-pressure turbine rotor speed sensor 10. The rotational speed of the high-pressure rotor is about 14000 - 16000 rpm.

[0062] In the present disclosure, when using the test equipment to test the high-pressure turbine rotor, first, the aeroengine needs to be modified, that is, the low-pressure turbine 8 and the low-pressure turbine rear casing 9 are removed, and the original tailpipe center cone is updated to a high-pressure test tailpipe center cone. That is to say, only the aeroengine core engine test piece shown within the rectangular frame is tested. The following will be specifically described in conjunction with Figure 3 for specific description.

[0063] Although the turbofan aeroengine is described as a preferred embodiment in this detailed description, those skilled in the art will understand that the equipment and system of the present disclosure for testing the high-pressure turbine rotor of an aeroengine are also applicable to other aeroengines, such as but not limited to turbojet aeroengines, turboprop aeroengines, turboshaft aeroengines, hybrid aeroengines, and so on.

[0064] Figure 2Schematic diagram of a device 200 for providing signal transmission according to an embodiment of the present disclosure is shown. In one embodiment, the device 200 may include: a transfer shaft 201, a rotor member 202 ( Figure 2 not shown in Figure 6a and 6b as shown), a stator member 203 ( Figure 2 not shown in Figure 6a and 6b as shown).

[0065] In one example, the device 200 may further include a stator support member 205, as Figure 2 shown. In some cases, the stator support member 205 may be circumferentially connected to the stator member 203. Specifically, the stator support member 205 may be connected to the stator member 203 via one or more connecting members (such as bolts, etc.). In another implementation, the stator support member 205 may be integrally formed with the stator member 203 around the stator member 203. Although the stator support member 205 is shown in Figure 2 on the side of the stator member 203 close to the rotor member 202, the stator support member may also surround the middle or any position of the stator member 203 without departing from the scope of the present disclosure.

[0066] In one example, the device 200 may further include a lead 207. In some cases, the lead 207 may include a signal lead for obtaining a signal from the sensing part and a power lead for providing power excitation to the sensing part, etc.

[0067] In one implementation, the rotor member 202 may rotate along the central axis, as Figure 6a shown. One or more rotating conductive devices may be provided on the rotor member 202, and the rotating conductive devices on the rotor member 202 may be respectively connected to the first lead segment of the lead.

[0068] In one implementation, the stator member 203 may include one or more conductive devices, and one or more conductive devices on the stator member 203 may conductively contact one or more rotating conductive devices on the rotor member 202. Specifically, one or more rotating conductive devices on the rotor member 202 may slidably conductively contact one or more conductive devices of the stator member 203, that is, one or more rotating conductive devices on the rotor member 202 slide relative to one or more conductive devices while realizing signal transmission. In some cases, the conductive devices on the stator member 203 may be connected to the second lead segment of these leads, and the rotating conductive devices on the rotor member 202 and the corresponding conductive devices on the stator member 203 transmit signals between the first lead segment and the second lead segment.

[0069] In one implementation, the adapter shaft 201 may include a first section 2011 and a second section 2012, where the rotor member 202 is coupled between the second section 2012 of the adapter shaft and the stator member 203. Specifically, the rotor member 202 is mechanically coupled to the second section 2012 of the adapter shaft through a coupling (e.g., an arc-shaped hexagon head coupling), as Figure 5 shown. As Figure 4a shown, one or more holes 204 may be provided on the first section 2011 of the adapter shaft 201 to form a passage through the one or more holes 204 on the first section 2011. Further, at least a portion of the first section 2011 of the adapter shaft 201 may be in the form of a tapered tube. It will be appreciated that the arrangement of the holes may include, but is not limited to, multiple rows of holes arranged uniformly or non-uniformly. In some cases, multiple rows of holes may be arranged uniformly or non-uniformly on the first section 2011, as Figure 4b shown.

[0070] During the actual use of the device 200, since a large amount of heat will be generated when one or more rotating conductive devices are in conductive contact with one or more conductive devices, a cooling pipeline may be introduced to cool one or more rotating conductive devices, thereby ensuring the reliability of the rotating conductive devices while extending their lifespan. The device 200 may optionally include a cooling pipeline 208.

[0071] In some cases, the cooling pipeline 208 includes a cooling intake pipe and a cooling return pipe. In these cases, the cooling intake pipe may be used to introduce cold air into one or more rotating conductive devices through the stator member 203, while the cooling return pipe is used to draw the cold air out of one or more rotating conductive devices through the stator member 203.

[0072] In other cases, the cooling pipeline 208 may include a cooling intake pipe and at least a portion of the cooling return pipe, or only include the cooling intake pipe. In these cases, the stator member may further include a cooling sandwich 206, where the rotor member 202 and the stator member 203 may be disposed in the cooling sandwich 206. Similarly, the cooling pipeline 208 (specifically, the cooling intake pipe) may be used to introduce cold air into one or more rotating conductive devices through the stator member 203. The cold air may not flow out from the cooling pipeline 208 (e.g., the cooling return pipe), but through the cooling sandwich 206, as Figure 7 shown. Alternatively, a portion of the cold air may be drawn out of one or more rotating conductive devices through the stator member 203 using the cooling pipeline 208 (e.g., at least a portion of the cooling return pipe), while another portion of the cold air may flow out through the cooling sandwich, both of which can save the pipeline passing through the center of the rotating shaft and save the pipeline. In one implementation, one end of the cooling sandwich 206 may be connected to the stator support member 205.

[0073] While the air-cooling method is described as an example in the present disclosure, those skilled in the art will appreciate that other cooling methods can also be applied to the present disclosure without departing from the scope of the present disclosure. In some cases, cold air can be introduced from ground equipment. In other cases, cold air can be introduced from the compressor.

[0074] In the present disclosure, since the device 200 is installed at the rear end of the high-pressure turbine rotor, the second lead segment of the lead 207 and the cooling pipeline 208 are introduced or led out from the stator member 203 of the device 200 attached to the rear end of the high-pressure turbine rotor, significantly shortening the length of the lead or pipeline. In addition, since the second lead segment of the lead 207 and the cooling pipeline 208 led out from or introduced into the stator member pass through the high-pressure test tailpipe center cone along the axis center and are taken out from the outlet of the high-pressure test tailpipe center cone and connected to the ground equipment, it will be easy to provide power excitation for one or more sensing parts, obtain signals from one or more sensing parts, and / or provide cold air for one or more devices for signal transmission, as further described in conjunction with Figure 3 the assembly schematic diagram below.

[0075] Figure 3 FIG. is an assembly schematic diagram for connecting the device 200 for signal transmission to the rear end of the high-pressure turbine rotor of an aeroengine according to an embodiment of the present disclosure. For example, as Figure 3 shown, Figure 2 the device 200 shown in Figure 1 can be connected to the rear end of the high-pressure turbine rotor of the core engine test piece of the aeroengine shown in Figure 1 (for example, connected to the shaded area 307 shown in Figure 1 ), and the stator member installation location and the rotor member installation location are also as shown in

[0076] to test various parameters of the high-pressure turbine rotor under working conditions, such as but not limited to strain and temperature. Figure 3 As shown in Figure 5 the first section 2011 of the adapter shaft 201 can be connected to the rear end of the high-pressure turbine rotor of the aeroengine, and then the rotor member 202 can be mechanically coupled to the second section 2012 of the adapter shaft 201 through a coupling (for example, an arc-shaped hexagonal head coupling) so that the rotor member 202 can rotate together with the adapter shaft 201 and the high-pressure turbine rotor (as shown in

[0077] ), thereby transmitting the torque of the high-pressure turbine rotor to the rotor member 202. Specifically, in one embodiment, the device 200 can be plugged into the rear end of the high-pressure turbine rotor. In one example, the rear end of the high-pressure turbine rotor can be modified so that the first section 2011 of the adapter shaft 201 can be connected to the rear end of the high-pressure turbine rotor.

[0078] Although a mechanical coupling using a coupling is described in the present disclosure, those skilled in the art will appreciate that any other mechanical coupling of a connecting member capable of transmitting torque may also be applied to the present disclosure without departing from the scope of the present disclosure.

[0079] In one example, the stator support 205 of the device 200 may be fixed to the rear seal ring of the interstage casing (also referred to as the rear bearing casing), thereby fixing the stator member 203 to the interstage casing, that is, to the aeroengine, as Figure 8 shown. In addition, tightly fixing the stator support 205 to the interstage casing can prevent air from flowing out from here, thereby ensuring airtightness of the air path.

[0080] In one example, one end of the cooling sandwich 206 may be fixed to the stator support 205, and one end of the cooling sandwich 206 may be connected and fixed to the mounting edge 305 of the high-pressure test tail nozzle center cone inside the rear turbine casing, as Figure 3 shown. In some preferred cases, the cooling sandwich 206 may be fixedly connected to the stator support 205 using flange mounting edge bolts. In some cases, the cooling sandwich 206 may be in a conical tubular shape, as Figure 2 shown. Although an example cooling sandwich is shown in the present disclosure, Figure 2 those skilled in the art will appreciate that any cooling sandwich shape capable of allowing cold air to be exhausted from the outlet of the high-pressure test tail nozzle center cone through the rear turbine casing may be applied to the present disclosure without departing from the scope of the present disclosure.

[0081] On the rotor member side, one or more sensing parts may be pasted on one or more blades of the high-pressure turbine rotor and connected to the rotor member 202 through a first lead segment of the lead 207 for providing power excitation to or collecting signals from the one or more sensing parts, specifically one or more rotating conductive devices of the rotor member 202. On the stator member side, as Figure 3As shown, the second lead segment of the lead 207 for providing power excitation to one or more sensing parts or collecting signals from one or more sensing parts and the cooling pipeline 208 for cooling the rotating conductive device can be taken out together from one or more conductive devices of the stator part 203, and then pass through the center of the rotating shaft, pass through the low-pressure turbine rear casing 304, and be led out from the outlet 306 of the high-pressure test tailpipe center cone, and connected to ground equipment, such as but not limited to ground acquisition equipment, the acquisition system of the test bench, etc. That is to say, through the device 200, signals, energy, etc. can be transmitted between the ground equipment and the sensing parts via the first lead segment of the lead, the rotor part 202, the stator part 203, and the second lead segment of the lead. In some cases, the cold air can be supplied through the test bench. In other cases, the cold air can also be supplied through the compressor. In some cases, the lead 207 can be arranged by pasting and fixing along the road. In some other cases, the cooling pipeline 208 can be arranged in a similar way.

[0082] In one example, one or more holes 204 can be provided on the second segment 2012 of the adapter shaft 201 to form a passage (the high-pressure turbine rear bearing cavity sealing air path, as shown) that passes through one or more holes 204 on the first segment 2011, passes through the bearing housing (with holes inside), the inter-stage casing (with holes inside), and reaches the outlet of the high-pressure test tailpipe center cone. Figure 3 As shown. Under the normal working condition of the aero-engine, the high-pressure turbine rear bearing cavity discharges air by passing the air flow through the holes on the bearing housing and the holes on the inter-stage casing. When the ejector in the tailpipe center exhaust pipe sucks air, the pressure in the tailpipe center exhaust pipe increases, sealing the outer ring of the bearing housing, thus ensuring the sealing of the high-pressure turbine rear bearing cavity. When the adapter section without adding one or more holes is installed, the air flow (for example, the air flow in the high-pressure turbine center exhaust pipe) will be blocked by the adapter section, and the original air path will no longer be continuous, unable to ensure the sealing of the high-pressure turbine rear bearing cavity. Adding one or more holes 204 on the second segment 2012 of the adapter shaft 201 can ensure that during the test, the air flow (for example, the air flow in the high-pressure turbine center exhaust pipe) passes through one or more holes on the first segment 2011 of the adapter shaft 201, then passes through the holes on the bearing housing and the holes on the inter-stage casing and reaches the outlet of the high-pressure test tailpipe center cone. That is to say, after the modification, the sealing air path of the high-pressure turbine rear bearing cavity still remains unobstructed. That is, the passage passing through one or more holes 204 on the second segment 2012 of the adapter shaft 201 can be connected to the original high-pressure turbine rear bearing cavity sealing air path, so as to ensure that the high-pressure turbine rear bearing cavity sealing air path is still continuous when the adapter section is installed, thus ensuring the sealing of the high-pressure turbine rear bearing cavity. As described above, the adapter shaft 201 can be in the shape of a tapered tube. In one example case, one or more holes 204 can be round holes, or any other shape of holes, such as Figure 4bAs shown. In another example scenario, multiple rows of holes can be uniformly or non-uniformly arranged on the adapter shaft 201, such as Figure 4b As shown. The effective flow area of the holes can be designed such that: when the airflow flowing into and passing through the holes on the bearing housing and flowing out through the holes on the intermediate casing into the central exhaust pipe of the tail nozzle is aspirated by the ejector, the pressure in the central exhaust pipe of the tail nozzle is sufficient to seal the high-pressure turbine rear bearing cavity. The total area of the holes can be determined by calculating the effective flow area. When the holes are circular through-holes, the effective flow area of the holes can be calculated by the following formula:

[0083] Effective flow area = n * πr 2

[0084] where n is the number of holes and r is the diameter of the holes. Those skilled in the art will appreciate that as long as the effective flow area of the holes meets the above requirements, any number and any shape of holes can be arranged at any position on the adapter shaft 201 without departing from the scope of the present disclosure.

[0085] The following provides an embodiment of testing using a test system. In this embodiment, the first section of the adapter shaft can be connected to the rear end of the high-pressure turbine rotor, and the rotor part of the test equipment can be mechanically coupled to the second section of the adapter shaft through a coupling so that the rotor part rotates together with the adapter shaft and the high-pressure turbine rotor. The stator support can be fixedly installed on the intermediate casing. One end of the cooling sandwich can be fixed to the stator support, and the other end of the cooling sandwich can be fixed on the installation edge of the high-pressure test tail nozzle central cone inside the turbine rear casing.

[0086] In this embodiment, the first lead segment in the lead wire is connected to one or more sensing parts, and the second lead segment of the lead wire is led out from one or more conductive devices of the stator part, and then passes through the low-pressure turbine rear casing along the axis center of the rotating shaft and is led out from the outlet of the high-pressure test tail nozzle central cone and connected to the ground equipment. That is, the first lead segment and the second lead segment of the lead wire are conducted through one or more rotating conductive devices and one or more conductive devices. In some cases, one or more sensing parts may include temperature sensing parts and strain sensing parts, etc. It will be appreciated that the temperature sensing parts and strain sensing parts here are only examples, and the test system of the present disclosure can include any type of sensing parts for testing any type of signals.

[0087] In this embodiment, the power supply excitation lead in the lead wire is connected to the power supply excitation to provide power supply excitation for the blades pasted on the high-pressure turbine rotor through the equipment for signal transmission.

[0088] After the installation is completed in the general assembly stage, connect the data acquisition equipment, start the aero-engine test run, start to supply cold air through the cooling pipeline, and monitor and collect the test signals of the dynamic stress and temperature of the high-pressure turbine rotor.

[0089] During actual use, installing the test equipment at the front end of the aero-engine will result in problems such as too long lead wire length, easy damage in the working environment, and test signal accuracy. Installing the test equipment at the rear end of the aero-engine may not meet the requirements for sealing the rear bearing cavity of the high-pressure turbine. The device for signal transmission provided by the present disclosure is installed at the rear end of the high-pressure turbine rotor of the aero-engine. By opening holes in the adapter shaft of the device to add an axial air path, the sealing of the rear bearing cavity of the high-pressure turbine is ensured. Thus, while installing the device at the rear end of the aero-engine, opening holes in the adapter shaft of the device to add an axial air path can solve the test difficulties introduced by installing at the rear end.

[0090] The present disclosure can achieve some of the above technical effects only by adaptively modifying the rear shaft and rear seal of the high-pressure turbine rotor and installing a high-pressure test tail nozzle center cone. These modified components are easy to replace, do not require spare parts, and reliably ensure the strain and temperature measurement of the high-pressure turbine rotor in the working state. When measurement is not required, only the high-pressure test tail nozzle center cone needs to be removed, and the rear shaft and rear seal of the high-pressure turbine rotor are replaced back.

[0091] Those skilled in the art can clearly understand that for the convenience and brevity of description, the specific working processes of the above-described devices and systems can refer to the corresponding processes in the foregoing system embodiments, and will not be described herein again.

[0092] Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present disclosure, and are not intended to limit them; although the present disclosure has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present disclosure, and they should all be covered by the scope of the claims and the description of the present disclosure.

Claims

1. A device for providing signal transmission, comprising: a rotor member, wherein the rotor member is provided with one or more rotating conductive devices; a stator member, the stator member comprising one or more conductive devices, wherein the one or more conductive devices on the stator member conductively contact the one or more rotating conductive devices on the rotor member; as well as An adapter shaft comprising a first section and a second section, wherein the rotor member is coupled between the second section of the adapter shaft and the stator member, wherein the first section of the adapter shaft is provided with one or more holes to form a passage passing through the one or more holes on the first section, and wherein the first section is connected to a rear end of a high-pressure turbine rotor of an aircraft engine.

2. The device according to claim 1, wherein The one or more holes on the first section of the adapter shaft include: Multiple rows of holes are evenly or unevenly arranged on the first section.

3. The device according to claim 1, wherein Further including: a stator support member, the stator support member surrounding the stator member; a cooling jacket having one end connected to the stator support; and A cooling pipeline is provided, wherein the cooling pipeline is led through the stator component to the rotating conductive device on the rotor component.

4. The device according to claim 1, wherein The rotating conductive device on the rotor component is connected to a first lead segment of the lead, and the conductive device on the stator component is connected to a second lead segment of the lead, wherein the rotating conductive device on the rotor component and the corresponding conductive device on the stator component transmit signals between the first lead segment and the second lead segment.

5. A test system for testing a high-pressure turbine rotor of an aircraft engine, comprising: The apparatus for providing signal transmission according to any one of claims 1 to 4, wherein: The first section of the adapter shaft is connected to the high-pressure turbine rear shaft. The rotor member is mechanically coupled to the second section of the transfer shaft via a coupling so as to rotate together with the transfer shaft and the high-pressure turbine rotor, and The device for providing signal transmission is fixed on the aircraft engine.

6. The test system according to claim 5, wherein: Further including: One or more sensed parts are attached to the high-pressure turbine rotor, wherein the one or more sensed parts are connected to one or more rotating conductive devices on the rotor component through a first lead segment of a lead.

7. The test system according to claim 5, wherein: The second lead section of the lead is led out from one or more conductive devices of the stator component of the equipment, and then passes through the high-voltage test tail jet center cone along the center of the rotating shaft and is connected out from the high-voltage test tail jet center cone outlet, wherein the lead includes a lead for obtaining a signal from the sensed part and a lead for providing power excitation to the sensed part.

8. The test system according to claim 5, wherein: The passage passing through one or more holes on the first section extends through the holes on the bearing seat and the holes on the interstage casing to the outlet of the central cone of the high-pressure test tail nozzle.

9. The test system according to claim 5, wherein: The device for providing signal transmission is fixed on the aircraft engine and further includes: The stator support of the stator member of the device is fixed to the rear seal inside the interstage casing; and One side of the cooling interlayer of the device is fixed on the stator support, and the other side of the cooling interlayer is overlapped on the inner wall of the central cone of the high-pressure test tail nozzle.

10. The test system according to claim 5, wherein: A cooling pipe is used to guide the cold air at the rotating conductive device on the rotor component to flow out of the cooling interlayer.

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