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

Abstract

This disclosure relates to an apparatus and system for testing a low-pressure turbine rotor of an aero-engine. The apparatus includes: a rotor component having one or more rotating conductive devices; a stator component including one or more conductive devices, wherein the one or more conductive devices on the stator component electrically contact the one or more rotating conductive devices on the rotor component; and a transition section assembly including a first section and a second section, with the rotor component coupled between the second section of the transition section assembly and the stator component. At least a portion of the transition section assembly, the rotor component, and the stator component are disposed within a housing, and the second section of the transition section assembly has one or more holes to form a passage from the interior of the first section of the transition section assembly through the one or more holes on the second section to an opening in the housing. The testing apparatus of this disclosure is connected to the rear end of a low-pressure turbine rotor, and an additional axial air passage is provided by opening a hole in the second section of the transition section assembly to ensure a tight seal of the rear bearing cavity of the entire engine.

Description

Technical Field

[0001] This disclosure relates to the field of aero-engines, and more specifically to an apparatus and system for testing low-pressure turbine rotors of aero-engines. Background Technology

[0002] Precise measurement and data acquisition of in-situ surface temperature and strain of key structural components of aero engines are crucial for improving aero engine efficiency, enhancing reliability, reducing emissions, designing new aero engines, and ensuring successful test runs.

[0003] During aero-engine testing, sensing elements (e.g., temperature and strain sensors) need to be mounted on the surface of the rotor blades and rotate at high speed with the rotor. This can make it difficult to transmit measurement signals from the sensing elements to ground equipment for processing, analysis, and storage. Furthermore, providing power excitation to the sensing elements that rotate at high speed with the rotor during testing also presents challenges.

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

[0005] The following provides a brief overview of one or more aspects to offer a basic understanding of such aspects. This overview is not an exhaustive summary of all conceived aspects, nor is it intended to identify the key or decisive 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 an introduction to the more detailed description that follows.

[0006] The purpose of this disclosure is to provide an apparatus and system for testing low-pressure turbine rotors of aircraft engines.

[0007] In one aspect, a device for providing signal transmission may include:

[0008] A rotor component, wherein one or more rotating conductive devices are provided on the rotor component;

[0009] A stator, the stator including one or more conductive devices, wherein the one or more conductive devices on the stator are electrically in contact with the one or more rotating conductive devices on the rotor; and

[0010] A transition section assembly, comprising a first section and a second section, wherein the rotor component is coupled between the second section of the transition section assembly and the stator component.

[0011] At least a portion of the transition section assembly, the rotor member, and the stator member are disposed within the housing, and

[0012] The second segment of the transition section assembly is provided with one or more holes to form a passage from the interior of the first segment of the transition section assembly through the one or more holes on the second segment to an opening in the housing.

[0013] The device for providing signal transmission may further include: a cooling inlet pipe and a cooling return pipe, wherein the cooling inlet pipe is introduced into a rotating conductive device on the rotor through the stator, and the cooling return pipe is led out from the rotating conductive device on the rotor through the stator.

[0014] In one example, the one or more holes on the second segment of the transition segment assembly include:

[0015] Multiple rows of holes are evenly or non-uniformly arranged on the second section.

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

[0017] In yet another example, the opening on the housing is located at the distal end of the rotor.

[0018] On the other hand, a test system for testing low-pressure turbine rotors of aircraft engines may include:

[0019] The device for providing signal transmission as described above is connected to the low-pressure turbine rotor, wherein the rotor components are mechanically coupled to the low-pressure turbine rotor via a first section of the transition section assembly and rotate together with the low-pressure turbine rotor, and the stator components are fixed to the aero-engine.

[0020] One or more sensing parts are attached to the low-pressure turbine rotor, and the one or more sensing parts are connected to one or more rotating conductive devices on the rotor via a first lead segment of a lead wire.

[0021] In one example, a second lead segment of the lead wire extends from one or more conductive devices of the stator and passes through a support plate of the low-pressure turbine rear gate to connect to ground equipment, wherein the lead wire includes a lead wire for acquiring signals from the sensing element and a lead wire for providing power excitation to the sensing element.

[0022] In another example, the opening of the housing is connected to the center exhaust pipe of the aircraft engine, such that a passage from inside the first section of the transition section assembly through one or more holes on the second section to the opening of the housing extends to the outlet of the center exhaust pipe.

[0023] In yet another example, the stator fixed to the aircraft engine further includes:

[0024] The stator is fixed inside the turbine rear brake of the aero-engine on the mounting edge of the tail nozzle center cone.

[0025] In yet another example, the first segment of the transition section assembly is provided with an internal spline, wherein the rotor component is mechanically coupled to the low-pressure turbine rotor via the first segment of the transition section assembly, further comprising:

[0026] The rotor component is coupled to the low-pressure turbine rotor via the internal spline on the first section of the transition section assembly and the external spline on the low-pressure turbine shaft exhaust pipe of the low-pressure turbine rotor.

[0027] This disclosure connects test equipment to the low-pressure turbine rotor of an aero-engine. The test equipment may include a transition section assembly, a rotor component, and a stator component. The rotor component is coupled to the rear end of the low-pressure turbine rotor (i.e., the low-pressure turbine shaft exhaust pipe) via the transition section assembly and rotates with the low-pressure turbine rotor. The stator component is fixed to the aero-engine. In this disclosure, a hole can be opened in the transition section assembly to add a shaft air passage to ensure the sealing of the rear bearing cavity of the entire engine. In this disclosure, lead wires and cooling pipes pass through the support plate of the rear casing of the low-pressure turbine and connect to the airborne safety test system, test bench, and ground equipment with the shortest possible length.

[0028] This disclosure couples the test equipment to the rear end of the low-pressure turbine rotor, significantly shortening the length of lead wires and cooling pipes, making them less prone to damage during rotation and significantly extending their service life, thereby ensuring the accuracy, reliability, and stability of signal measurements. Furthermore, when measurements of the aero-engine are not required, only the low-pressure turbine shaft exhaust pipe, the tail nozzle center exhaust pipe, and the low-pressure turbine rear casing mounting bracket need to be replaced, making replacement convenient and easy to operate.

[0029] This summary is provided to introduce some concepts in a simplified form, which will be further described in the detailed description below. This summary is not intended to identify key or essential features of the claimed subject matter, nor is it intended to limit the scope of the claimed subject matter. Other aspects, features, and / or advantages of the embodiments will be set forth in part in the description which follows, and will be apparent in part from the description, or may be learned by practice of the invention. Attached Figure Description

[0030] To gain a more detailed understanding of the features described above in this disclosure, reference can be made to a more specific description of the above-briefly summarized aspects, some of which are illustrated in the accompanying drawings. However, it should be noted that the drawings illustrate only certain typical aspects of this disclosure and should not be considered as limiting its scope, as other equivalent aspects are permissible in this description. In the drawings:

[0031] Figure 1 A schematic diagram of the low-pressure rotor of an aero-engine is shown.

[0032] Figure 2 A schematic diagram of a device for providing signal transmission according to an embodiment of the present disclosure is shown; and

[0033] Figure 3 This is an assembly diagram illustrating the connection of a device for providing signal transmission to a low-pressure turbine rotor of an aircraft engine according to an embodiment of the present disclosure.

[0034] Figure 4 A schematic diagram is shown of an internal spline on a transition section assembly according to an embodiment of the present disclosure coupled to an external spline on a low-pressure turbine shaft exhaust pipe of an aero-engine;

[0035] Figure 5 A schematic diagram of the hole distribution on a transition section assembly according to an embodiment of the present disclosure is shown;

[0036] Figure 6 A schematic diagram of another hole distribution on a transition section assembly according to an embodiment of the present disclosure is shown; and

[0037] Figure 7 A schematic diagram of the housing of a device for providing signal transmission according to an embodiment of the present disclosure is shown.

[0038] The labels in the attached diagram are:

[0039] 1. Fan, 2. Supercharger stage, 3. Intermediate casing, 4. High-pressure compressor, 5. Combustion chamber, 6. High-pressure turbine, 7. Interstage casing, 8. Low-pressure turbine, 9. Low-pressure turbine rear casing, 10. Low-pressure turbine rotor speed sensor.

[0040] Device 200 for providing signal transmission, transition section assembly 201, rotor component 202, stator component 203, one or more holes 204, housing 205, lead wire 206, cooling pipe 207, opening 208; and

[0041] The low-pressure turbine rotor 301, the rear bearing cavity of the whole machine 302, the mounting edge of the tail nozzle center cone 303, and the support plate of the low-pressure turbine rear casing 304. Detailed Implementation

[0042] The specific embodiments described below with reference to the accompanying drawings are intended as descriptions of various configurations and are not intended to represent only the configurations in which the concepts described herein can be practiced. This specific embodiment includes detailed specifications 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 detailed specifications.

[0043] Based on these teachings, those skilled in the art will understand that the scope of this invention is intended to cover any aspect of the invention, whether implemented independently of or in combination with any other aspect of the invention. For example, any number of the aspects described can be used to implement an apparatus or system. Furthermore, the scope of this invention is intended to cover such apparatuses or systems practiced using other structures, functionalities, or structures and functionalities that complement or differ from the aspects of the described invention.

[0044] While specific aspects have been described herein, numerous variations and substitutions of these aspects fall within the scope of the invention. Although some benefits and advantages of preferred aspects have been mentioned, the scope of the invention is not intended to be limited to a particular benefit, use, or objective. The detailed description and accompanying drawings are merely illustrative and not limiting of the invention, and the scope of the invention is defined by the appended claims and their equivalents.

[0045] During aero-engine testing, sensing elements (e.g., temperature and strain sensing elements) need to be mounted on the surface of the rotor blades and rotate with the rotor. This can make it difficult to transmit measurement signals from the sensing elements to the onboard safety testing system, test bench, or ground equipment for processing, analysis, and storage. Furthermore, providing power excitation to the sensing elements that rotate with the rotor during testing also presents challenges.

[0046] However, the strain and temperature of low-pressure turbine rotor blades fall under airworthiness standards, and aero-engine manufacturers must provide relevant test data on the dynamic stress of the low-pressure turbine rotor under various operating conditions. If the test data meets the margin requirements—meaning the low-pressure turbine rotor blades meet relevant standards—the probability of damage or breakage during flight is significantly reduced. Therefore, testing the low-pressure turbine rotor under various operating conditions (especially during test runs) is essential.

[0047] To address one or more technical problems existing in the prior art, this disclosure proposes a test system for testing a low-pressure turbine rotor of an aero-engine, comprising: equipment for providing signal transmission and one or more sensing elements. The equipment for providing signal transmission may include a transition section assembly, a rotor component, and a stator component, wherein the rotor component may be provided with one or more rotating conductive devices, and the stator component may include one or more conductive devices. The test system may optionally include ground equipment, such as, but not limited to, an airborne safety test system, a test bench acquisition system, or other ground acquisition systems, etc.

[0048] Generally, the sensing element can be attached to the blades of the low-pressure turbine rotor and connected to one or more rotating conductive devices of the rotor component via a first lead segment of a lead wire. These rotating conductive devices electrically contact one or more conductive devices of the stator component. A second lead segment of the lead wire extends from one or more conductive devices of the stator component, passes through a support plate of the low-pressure turbine's rear gate, and connects to ground equipment, such as, but not limited to, a test bench's acquisition system or other ground acquisition systems. In other words, the measurement signal from the sensing element can be transmitted to the ground equipment via the first lead segment, the rotating conductive devices of the rotor component, the conductive devices of the stator component, and the second lead segment.

[0049] The device used for providing signal transmission is an electrical component responsible for connecting and transmitting power and signals to a rotating body. Although the structure of the device used for providing signal transmission is not specifically shown in the accompanying drawings, those skilled in the art will understand that it is typically mounted at the center of rotation of the device under test and consists of a rotating part, a stationary part, and accessory parts. The rotating part is connected to the rotating structure under test and rotates with it, and is called the "rotor," while the stationary part is connected to the fixed structure of the device and is called the "stator."

[0050] For example, a slip ring can be used to provide signal transmission. Also known as a rotary electrical interface or electrical rotary joint, a slip ring can be used in scenarios requiring unrestricted continuous rotation while simultaneously transmitting power or data from a rotating position to a fixed position. The slip ring as a whole relies on the principles of elastic overlap, rolling overlap, or sealing, along with ingenious motion and sealing structure design, precise component manufacturing, and appropriate material selection to form a stable and reliable rotary communication system. For instance, a slip ring can utilize the sliding or rolling contact, electrostatic coupling, or electromagnetic coupling of conductive components to transmit electrical signals and energy between rotating and stationary parts. Rotating parts contain driving, measuring, and control elements, to which control signals and power must be supplied. This necessitates various slip ring assemblies to transmit signals and energy. The number of circuits requiring rotary connections can exceed one hundred; the structural design must first ensure reliable contact and guarantee continuous connection of all circuits.

[0051] By attaching the rotating body of a slip ring to an infinitely rotating device, power can be supplied to the rotating body, enabling it to perform detection and testing while rotating indefinitely. A slip ring can collect data from up to 150 measurement points (e.g., 300 connected lines) while ensuring clear and interference-free signal transmission to ground equipment. Depending on the transmission medium, devices used for signal transmission can be categorized as electrical slip rings, fluid slip rings, smooth rings, etc. It is worth noting that although an electrical slip ring is used as an example in this disclosure, any type of device capable of transmitting signals from a rotor to a stator is applicable to this disclosure.

[0052] In the test system described in this disclosure, the device for providing signal transmission is designed to be installed at the rear end of the low-pressure turbine rotor. Therefore, the total length of the lead wire from one or more sensing elements to the ground device is much shorter than the total length in the case where the device for providing signal transmission is installed at the front end of the low-pressure turbine rotor. This ensures the service life of the test system and guarantees the stability, accuracy, and reliability of the test signal.

[0053] Furthermore, in the device for providing signal transmission described in this disclosure, one or more holes may be provided on the second section of the transition section assembly to form a passage from the interior of the first section of the transition section assembly through one or more holes in the second section to the opening of the housing. That is, airflow can flow from the interior of the first section of the transition section assembly through one or more holes in the second section into the housing and flow along the housing to the opening of the housing.

[0054] The following description will be provided in conjunction with the accompanying drawings.

[0055] As an example, Figure 1 A schematic diagram of the low-pressure rotor of an aero-engine is shown. Figure 1 As shown, an aero-engine may 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 interstage casing 7, a low-pressure turbine 8, a low-pressure turbine rear casing 9, and a low-pressure turbine rotor speed sensor 10. The low-pressure rotor speed is approximately 3000–5000 RPM. Under normal operating conditions, the rear bearing cavity of the entire engine is sealed by exhaust gas drawn from the exhaust pipe of the tail nozzle through the grates on the low-pressure turbine shaft exhaust pipe and the low-pressure turbine structural components simultaneously by the ejector.

[0056] Although the preferred embodiment is described in this detailed description using a turbofan aero engine, those skilled in the art will understand that the apparatus and system disclosed herein for testing the low-pressure turbine rotor of an aero engine are also applicable to other aero engines, such as, but not limited to, gas turbine aero engines.

[0057] Figure 2A schematic 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 transition section assembly 201, a rotor 202, a stator 203, and a housing 205. At least a portion of the transition section assembly 201, the rotor 202, and the stator 203 may be disposed in the housing 205.

[0058] In one example, device 200 may further include lead 206. In some cases, lead 206 may include signal leads for acquiring signals from the sensing part and power leads for providing power excitation to the sensing part, etc.

[0059] In a preferred example, device 200 may further include a stator support assembly. In a further example, device 200 may include a spoke mounting structure connected to the stator support assembly.

[0060] In one implementation, rotor 202 can rotate along the central axis, such as Figure 2 As shown in the figure. The rotor 202 may be provided with one or more rotating conductive devices, wherein the rotating conductive devices on the rotor 202 can be respectively connected to the first lead segment of the lead wire.

[0061] In one implementation, the stator 203 may include one or more conductive devices, wherein the one or more conductive devices on the stator 203 can electrically contact one or more rotating conductive devices on the rotor 202. Specifically, the one or more rotating conductive devices on the rotor 202 can slidably conductively contact the one or more conductive devices on the stator 203, that is, the one or more rotating conductive devices on the rotor 202 slide relative to one or more conductive devices while simultaneously transmitting signals. In some cases, the conductive devices on the stator 203 may be connected to a second lead segment of these leads, wherein the rotating conductive devices on the rotor 202 and the corresponding conductive devices on the stator 203 transmit signals between the first lead segment and the second lead segment.

[0062] In one implementation, the transition section assembly 201 may include a first section and a second section, wherein the rotor member 202 is coupled between the second section of the transition section assembly and the stator member 203. The first section of the transition section assembly 201 may have an internal spline. The second section of the transition section assembly 201 may have one or more holes 204 to form a passage from the interior of the first section of the transition section assembly 201 through one or more holes 204 on the second section to an opening 208 of the housing 205. In some cases, the opening 208 of the housing 205 may be located at the distal end of the rotor member 202. In some cases, at least a portion of the second section of the transition section assembly 201 may be tapered. 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 one case, multiple rows of holes may be uniformly arranged on the second section 203 (e.g., Figure 5 (As shown). In another case, multiple rows of holes can be non-uniformly arranged on the second segment 203 (e.g. Figure 6 (As shown).

[0063] In a preferred embodiment, device 200 may optionally include a cooling conduit 207. The cooling conduit 207 may include a cooling inlet pipe and a cooling return pipe. In actual operation of device 200, since one or more rotating conductive devices generate a large amount of heat when in conductive contact with one or more conductive devices, a cooling conduit can be introduced to cool the one or more rotating conductive devices, thereby extending the lifespan of the rotating conductive devices while ensuring their reliability. Although air cooling is described as an example in this disclosure, those skilled in the art will appreciate that other cooling methods can also be applied to this disclosure without departing from its scope. In a preferred embodiment, the cooling inlet pipe can be introduced into one or more rotating conductive devices through stator 203, and the cooling return pipe can be led out from one or more rotating conductive devices through stator 203. In some cases, cool air can be introduced from ground equipment. In other cases, cool air can be introduced from a compressor.

[0064] In this disclosure, since the device 200 is installed at the rear end of the low-pressure turbine rotor, the second lead segment of the lead wire 206 and the cooling pipe 207 are introduced or led out from the stator 203 of the device 200 attached to the rear end of the low-pressure turbine rotor, significantly shortening the length of the lead wire or pipe. Furthermore, since the second lead segment of the lead wire 206 and the cooling pipe 207, introduced or led out from the stator, pass through the support plate 304 of the low-pressure turbine rear brake and connect to ground equipment, it is easy to provide power excitation to one or more sensing elements, obtain signals from one or more sensing elements, and / or provide cooling air to one or more devices used for signal transmission, as described below. Figure 3 The assembly diagram will be used for further description.

[0065] Figure 3 This is an illustration of an assembly diagram showing the connection of a device 200 for providing signal transmission to the low-pressure turbine rotor of an aircraft engine according to an embodiment of the present disclosure. For example, as... Figure 3 As shown, Figure 2 The device 200 shown can be accessed Figure 1 The low-pressure turbine rotor of the aircraft engine shown (e.g., connected to) Figure 3 The shaded area (305 shown in the diagram) is used to test various parameters of the low-pressure turbine rotor under operating conditions, such as, but not limited to, strain and temperature.

[0066] like Figure 3 As shown, the rotor 202 can be mechanically coupled to the low-pressure turbine rotor 301 (rear end) of the aero-engine via the adapter section assembly 201 so that the rotor 202 can rotate together with the low-pressure turbine rotor 301, thereby transmitting the torque of the low-pressure turbine rotor 301 to the rotor 202.

[0067] Specifically, in one embodiment, the originally connected shaft exhaust pipe and tailpipe center exhaust pipe can be separated, and the device 200 can be coupled between the shaft exhaust pipe and the tailpipe center exhaust pipe. In one example, the shaft exhaust pipe can be modified, for example, by providing an external spline inside the shaft exhaust pipe wall. As described above, the first section of the transition section assembly 201 can be provided with an internal spline. Thus, the rotor 202 can be mechanically coupled to the low-pressure turbine shaft exhaust pipe via the transition section assembly 201 through the internal and external splines to rotate together with the low-pressure turbine rotor 301 (e.g., ...). Figure 4 (As shown). Although a mechanical coupling method using internal and external splines is described in this disclosure, those skilled in the art will appreciate that any other mechanical coupling method that enables the rotor 202 to be mechanically coupled to and rotate with the low-pressure turbine rotor 301 can also be applied to this disclosure without departing from its scope.

[0068] In one example, the stator 203 of device 200 can be fixed to an aircraft engine. In some preferred embodiments, the stator 203 can be fixed to the aircraft engine using a flange mounting edge bolt connection. In other preferred embodiments, the stator 203 can use a spoke mounting structure connected to the stator support assembly (see...). Figure 2 It is bolted to the aircraft engine. In other preferred embodiments, the stator 203 can be connected and fixed to the mounting edge 303 of the tail nozzle center cone inside the turbine rear casing (see [reference]). Figure 1 )superior.

[0069] On the rotor side, one or more sensing elements can be attached to one or more blades of the low-pressure turbine rotor 301 and connected to the rotor 202 via a first lead segment of lead 206 for providing power excitation to or acquiring signals from the one or more sensing elements, specifically one or more rotating conductive devices of the rotor 202. On the stator side, such as Figure 3 As shown, the second lead segment of lead wire 206, used to provide power excitation to one or more sensing elements or to acquire signals from one or more sensing elements, and the cooling pipe 207 for cooling the rotating conductive device, can be led out together from one or more conductive devices of the stator 203 and then pass through the support plate 304 of the low-pressure turbine rear casing to connect to ground equipment, such as, but not limited to, ground acquisition equipment, test bench acquisition system, etc. That is, through device 200, signals and energy can be transmitted between the sensing elements and ground equipment via the first lead segment of lead wire, rotor 202, stator 203, and the second lead segment of lead wire. In some cases, cold air can be supplied through a test bench. In other cases, cold air can also be supplied through a compressor. In some cases, lead wire 206 can be laid out by adhesive bonding. In other cases, cooling pipe 207 can be laid out in a similar manner.

[0070] As is known to those skilled in the art, support plates are generally designed in a streamlined shape to maximize the efficiency of the internal flow path. If the second lead segment of lead wire 206 and the cooling pipe 207 are located outside the support plate, it may affect the efficiency of the internal flow path and cause thrust loss, resulting in a difference from the actual operating state of an aero-engine. The second lead segment of lead wire 206 and the cooling pipe 207 pass through the support plate 304 of the low-pressure turbine rear casing to avoid affecting the airflow path and to maximize the simulation of the actual operating state of an aero-engine.

[0071] In one example, the second segment of the transition section assembly 201 may be provided with one or more holes 204 to form a passage (axial air passage, such as) from the interior of the first segment of the transition section assembly 201 through one or more holes 204 of the second segment to the opening 208 of the housing 205. Figure 3 (As shown). Furthermore, the opening 208 of the housing 205 can be connected to the tailpipe center exhaust pipe to form an exhaust passage. Preferably, the opening 208 of the housing can be bolted to the tailpipe center exhaust pipe forming the exhaust passage. That is, during actual operation, airflow (e.g., airflow in the low-pressure turbine shaft exhaust pipe) can flow from the inside of the first section of the transition section assembly 201 through one or more holes 204 on the second section into the housing 205, and within the housing 205, in the direction of the arrow (e.g., as shown). Figure 3The airflow (as shown in the diagram) flows from the opening 208 of the housing 205 to the central exhaust pipe of the tail nozzle. In this example, when the ejector in the central exhaust pipe draws air, the pressure in the central exhaust pipe increases, causing the outer bearing housing to seal. This ensures that the rear bearing cavity of the entire machine remains sealed during test runs even when the low-pressure turbine rotor (low-pressure turbine shaft exhaust pipe) is being modified for testing. More preferably, the central cone of the tail nozzle can enclose the housing 205, but a certain space is left between the central cone of the tail nozzle and the housing 205 to accommodate cooling pipes, test lines, etc.

[0072] Although this is published Figure 7 An example housing is shown, but those skilled in the art will appreciate that any housing shape capable of forming a passage from inside the first segment of the transition section assembly through one or more holes on the second segment to the opening of the housing can be applied to this disclosure without departing from its scope.

[0073] Furthermore, providing one or more holes 204 on the transition section assembly 201 creates a central air passage within the housing 205, thereby ensuring a tight seal of the rear bearing cavity of the entire machine. As described above, the transition section assembly 201 can be in the shape of a tapered tube. In one example, the one or more holes 204 can be circular holes or holes of any other shape. In another example, multiple rows of holes can be evenly arranged on the transition section assembly 201 (e.g., Figure 5 (As shown). In other example scenarios, multiple rows of holes may be provided non-uniformly on the transition section assembly 201 (e.g. Figure 6 (As shown). The effective flow area of ​​the orifice can be designed such that: when the airflow flowing into the housing from one or more orifices and out of the opening of the housing into the tail nozzle center exhaust pipe is drawn by the ejector, the pressure in the tail nozzle center exhaust pipe is sufficient to seal the rear bearing cavity 302 of the entire machine (as shown). Figure 1 (As shown). The total area of ​​the orifice can be determined by calculating the effective flow area. When the orifice is a circular through-hole, the effective flow area can be calculated using the following formula:

[0074] Effective flow area = n*πr 2 *sinα

[0075] Wherein, n is the number of holes, r is the diameter of the holes, and α is the angle between the transition section assembly 201 and the central axis of the low-pressure turbine rotor. 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 shape of holes can be provided at any position on the transition section assembly 201 without departing from the scope of this disclosure.

[0076] The following provides an example of testing using a test system. In this example, the rotor component of the device can be coupled to the low-pressure turbine rotor via an internal and external spline connection through a transition section assembly.

[0077] The stator can be bolted to the mounting edge 303 of the nozzle center cone inside the turbine rear casing using a spoke mounting structure on the stator support assembly. The nozzle center exhaust pipe is located after the opening of the housing, and the nozzle center cone encloses the housing. There is space between the nozzle center cone and the housing to accommodate cooling pipes, test lines, etc.

[0078] In this embodiment, a first lead segment of the lead wire is connected to one or more sensing elements, and a second lead segment of the lead wire extends from one or more conductive devices of the stator, passes through a support plate of the turbine rear casing, and connects to ground equipment. That is, the first and second lead segments of the lead wire are connected via one or more rotating conductive devices and one or more conductive devices. In some cases, the one or more sensing elements may include temperature sensing elements and strain sensing elements, etc. It will be understood that the temperature sensing elements and strain sensing elements described herein are merely examples, and the test system of this disclosure may include any type of sensing element for testing any type of signal.

[0079] In this embodiment, the power excitation lead in the lead wire is connected to a power excitation to provide power excitation to the blades attached to the low-pressure turbine rotor via a device for providing signal transmission.

[0080] After the final assembly is completed, the data acquisition equipment is connected, the aero-engine test run is started, and cool air is supplied through the cooling pipes to monitor and collect test signals of dynamic stress and temperature of the low-pressure turbine rotor.

[0081] In practical use, installing the test equipment at the front end of the aero-engine results in excessively long lead wires, which are prone to damage under operating conditions, and can lead to issues with the accuracy of test signals. Installing the test equipment at the rear end of the aero-engine may not meet the sealing requirements of the rear bearing cavity. The signal transmission device provided in this disclosure is installed at the rear end of the aero-engine. By adding a axial air passage through a hole in the device's transition section assembly, the sealing of the rear bearing cavity is ensured. This solves the testing difficulties associated with rear-end installation by allowing the device to be installed at the rear end of the aero-engine while simultaneously adding a axial air passage through the transition section assembly.

[0082] This invention discloses the ability to achieve some of the aforementioned technical effects by making adaptive modifications only to the low-pressure turbine rotor (low-pressure turbine shaft exhaust pipe), the support plate (internal) of the low-pressure turbine rear casing, and the central exhaust pipe of the tail nozzle. These modified components are easy to replace, require no spare parts, and reliably ensure strain and temperature measurement of the low-pressure turbine rotor under operating conditions. When measurements are not required, the aircraft engine can operate normally simply by replacing the low-pressure turbine shaft exhaust pipe and the central exhaust pipe of the tail nozzle, while simultaneously sealing the support plate of the low-pressure turbine rear casing.

[0083] Those skilled in the art will clearly understand that, for the sake of convenience and brevity, the specific working process of the devices and systems described above can be referred to the corresponding process in the foregoing system embodiments, and will not be repeated here.

[0084] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this application, and they should all be covered within the scope of the claims and specification of this application.

Claims

1. A device for providing signal transmission, comprising: A rotor component, wherein one or more rotating conductive devices are provided on the rotor component; A stator, the stator including one or more conductive devices, wherein the one or more conductive devices on the stator are electrically in contact with the one or more rotating conductive devices on the rotor; as well as A transition section assembly, comprising a first section and a second section, wherein the rotor component is coupled between the second section of the transition section assembly and the stator component. At least a portion of the first section of the transition section assembly is disposed outside the housing, and the second section of the transition section assembly, the rotor member, and the stator member are disposed within the housing. The second segment of the transition section assembly is provided with one or more holes to form a passage from the interior of the first segment of the transition section assembly through the one or more holes on the second segment to an opening in the housing.

2. The device as described in claim 1, characterized in that, Further includes: A cooling inlet pipe and a cooling return pipe, wherein the cooling inlet pipe is introduced into a rotating conductive device on the rotor through the stator, and the cooling return pipe is led out from the rotating conductive device on the rotor through the stator.

3. The device as described in claim 1, characterized in that, The one or more holes on the second segment of the adapter assembly include: Multiple rows of holes are evenly or non-uniformly arranged on the second section.

4. The device as described in claim 1, characterized in that, The rotating conductive device on the rotor is connected to the first lead segment of the lead wire, and the conductive device on the stator is connected to the second lead segment of the lead wire, wherein the rotating conductive device on the rotor and the corresponding conductive device on the stator transmit signals between the first lead segment and the second lead segment.

5. The device as described in claim 1, characterized in that, The opening on the housing is located at the distal end of the rotor.

6. A test system for testing low-pressure turbine rotors of aircraft engines, comprising: The device for providing signal transmission as described in any one of claims 1-5, the device being connected to the low-pressure turbine rotor, wherein the rotor component is mechanically coupled to the low-pressure turbine rotor via a first segment of a transition section assembly and rotates with the low-pressure turbine rotor, and the stator component is fixed to the aero-engine, wherein the device includes a lead wire comprising a first lead wire segment and a second lead wire segment; and One or more sensing parts are attached to the low-pressure turbine rotor, and the one or more sensing parts are connected to one or more rotating conductive devices on the rotor via the first lead segment.

7. The testing system as described in claim 6, characterized in that, The second lead segment extends from one or more conductive devices of the stator and passes through the support plate of the low-pressure turbine rear brake to connect to the ground equipment. The lead includes a lead for acquiring signals from the sensing element and a lead for providing power excitation to the sensing element.

8. The testing system as described in claim 6, characterized in that, The opening of the housing is connected to the center exhaust pipe of the aircraft engine, such that a passage from the interior of the first section of the transition section assembly through one or more holes on the second section to the opening of the housing extends to the outlet of the center exhaust pipe.

9. The testing system as described in claim 6, characterized in that, The stator component, fixed to the aero-engine, further includes: The stator is fixed inside the turbine rear brake of the aero-engine on the mounting edge of the tail nozzle center cone.

10. The testing system as described in claim 6, characterized in that, The first section of the transition section assembly is provided with an internal spline, wherein the rotor component is mechanically coupled to the low-pressure turbine rotor through the first section of the transition section assembly, further comprising: The rotor component is coupled to the low-pressure turbine rotor via the internal spline on the first section of the transition section assembly and the external spline on the low-pressure turbine shaft exhaust pipe of the low-pressure turbine rotor.

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