A measuring and mounting structure for the sensing part of the total temperature and total pressure at the turbine outlet of an aircraft engine

Abstract

The present application belongs to the technical field of total temperature and total pressure measurement at the outlet of an aircraft engine turbine, and specifically relates to a measurement and installation structure for the sensing part of the total temperature and total pressure at the outlet of an aircraft engine turbine, which mainly includes a support rod, a total temperature and total pressure composite measurement assembly, a movable sealing gasket, an outer support movable sealing assembly, an inner support sleeve, a pressure nozzle, an adapter, a thermocouple connector, an outer casing, and an inner casing. It can avoid leakage of the internal and external airflows while having the ability to compensate for the uncoordinated deformation between the outer casing and the inner casing.

Description

Technical Field

[0001] The present application belongs to the technical field of measuring the total temperature and total pressure at the turbine outlet of an aircraft engine, and specifically relates to a measuring and mounting structure for a sensing part of the total temperature and total pressure at the turbine outlet of an aircraft engine. Background Art

[0002] The total temperature and total pressure at the turbine outlet of an aircraft engine are important parameters for aircraft engine performance calculation and airborne health monitoring system, and are of great significance for evaluating aircraft engine performance and working status.

[0003] Currently, the following two methods are mainly used to measure the total temperature and total pressure at the turbine outlet of an aircraft engine:

[0004] A fixed, plug-in sensing element is installed in the outer casing. Its support rod passes through reserved holes in the outer and inner casings and extends into the inner casing to measure the total temperature and pressure at the turbine outlet. The angles and depths of the temperature and pressure sensing heads on the support rod are arranged in an equiannular or equidistant manner according to the measurement cross-section requirements. Considering the significant temperature difference between the inner and outer casing flow fields at the turbine outlet, the thermal expansion of the inner casing is much greater than that of the outer casing, and there is significant movement between the inner and outer casings. To prevent damage to the support rod due to uncoordinated deformation between the inner and outer casings, a certain amount of space is reserved in the reserved hole on the inner casing. This design causes the high-temperature, high-pressure inner casing airflow at the turbine outlet to leak into the outer casing airflow, affecting the overall performance of the aircraft engine. In addition, the support rod becomes a very long single cantilever support structure, which places high demands on the strength and rigidity of the support rod. Too thick will cause flow channel blockage, affecting the performance of the aircraft engine. Too thin will result in insufficient rigidity, causing bending and friction with the inner casing, endangering the safe operation of the aircraft engine.

[0005] A fixed plug-in sensing part is installed on the inner casing and extended into the inner casing to measure the total temperature and total pressure at the turbine outlet. The temperature and pressure measurement leads need to be led out of the outer casing through the aircraft engine support plate or special pipelines. This involves the modification of a large amount of aircraft engine structure, which is costly. The tail of the sensing part is directly exposed to the outer casing airflow, and there is a risk of the leads being blown out by the outer casing flow channel, resulting in low reliability. In addition, the sensing part needs to be installed during the aircraft engine assembly process, and generally cannot be replaced or repaired on site in the event of a failure, resulting in poor maintainability and interchangeability.

[0006] In the above-mentioned technical solution of installing a fixed plug-in sensing part on the outer casing and installing a fixed plug-in sensing part on the inner casing to measure the total temperature and total pressure at the turbine outlet, the temperature and pressure measuring heads on the sensing part are arranged at different radial positions, which is not conducive to subsequent data processing. The excessive number of openings on the support rod directly affects the strength of the support rod of the sensing part. The support rod is prone to fracture and failure due to stress concentration at the openings, threatening the safe operation of the aircraft engine.

[0007] This application is proposed in view of the above-mentioned technical defects.

[0008] It should be noted that the disclosure of the above background technology content is only used to assist in understanding the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of the present application. In the absence of clear evidence that the above content has been disclosed on the filing date of the present application, the above background technology should not be used to evaluate the novelty and creativity of the present application. Summary of the Invention

[0009] The purpose of the present application is to provide a measurement and installation structure for the sensing part of the total temperature and total pressure at the turbine outlet of an aircraft engine, so as to overcome or alleviate at least one of the technical defects of the known ones.

[0010] The technical solution of this application is:

[0011] A measuring and mounting structure for a sensing part of a total temperature and total pressure sensor at an aero-engine turbine outlet, comprising:

[0012] an outer casing having an outer casing measurement hole;

[0013] The inner casing is arranged inside the outer casing, and forms an outer casing with the outer casing, and the inner casing forms an inner casing, and has an inner casing measuring hole on the inner casing; the inner casing measuring hole is in a step shape;

[0014] The support rod has a lower end inserted into the inner casing through the inner casing measuring hole, and an upper end thereof has a circular boss; the circular boss is installed in the inner casing measuring hole;

[0015] Multiple total temperature and total pressure composite measurement components are axially connected to the windward side of the support rod and are located inside the interior, including a total pressure sensor and a thermocouple;

[0016] A movable sealing pad is sleeved on the upper end of the support rod;

[0017] The outer support movable seal assembly comprises an outer support sleeve, a sealing seat, an elastic sealing ring, a sealing pressure plate, and a sealing vibration damping ring, wherein the lower end of the outer support sleeve is screwed into the measuring hole of the inner casing to press the movable sealing gasket and the circular boss, the upper end extends out of the measuring hole of the outer casing, and the middle part is provided with an annular boss; the annular boss is provided with an annular positioning groove, in which an elastic sealing ring is arranged; the sealing seat is provided with a sealing hole and an annular sealing edge, and the sealing hole is sleeved on the annular boss; the sealing pressure plate is connected to the outer casing by bolts, and the sealing pressure plate is provided with an annular sealing groove, and the annular sealing edge is located in the annular sealing groove, and the radial dimension of the annular sealing edge is smaller than the radial dimension of the annular sealing groove; one end of the sealing vibration damping ring is extended into the end of the outer support sleeve extending out of the outer casing, and the other end has an outward annular folded edge;

[0018] One end of the inner support sleeve passes through the sealing vibration damping ring and extends into the outer support sleeve, and is connected to the upper end of the support rod;

[0019] An adapter, one end of which is connected to the other end of the inner support sleeve;

[0020] Multiple pressure nozzles are connected to the side wall of the adapter; the pressure pipeline of each total pressure sensing head is connected to each pressure nozzle through a support rod, an inner support sleeve, and the inside of the adapter;

[0021] A plurality of thermocouple connectors are connected to the other end of the adapter; the lead wires of the respective thermocouples are connected to the respective thermocouple connectors through the support rod, the inner support sleeve and the interior of the adapter.

[0022] According to at least one embodiment of the present application, in the above-mentioned aircraft engine turbine outlet total temperature and total pressure sensing part measurement and installation structure, high-temperature resistant hot cement is poured into the support rod to fix the pressure pipeline of the total pressure sensing head and the leads of each thermocouple.

[0023] According to at least one embodiment of the present application, in the above-mentioned aircraft engine turbine outlet total temperature and total pressure sensing part measurement and installation structure, the windward surface of the support rod has a plurality of composite measurement component installation holes arranged along its axial direction;

[0024] Each total temperature and total pressure composite measurement component also includes:

[0025] The composite fairing has a total pressure sensing head air inlet and a thermocouple air inlet at the front end, a total pressure sensing head exhaust hole and a thermocouple exhaust hole at the side wall, a total pressure sensing head mounting hole and a thermocouple mounting hole at the rear end, and a total pressure measurement space connected to the total pressure sensing head air inlet, the total pressure sensing head exhaust hole, and the total pressure sensing head mounting hole, and a total temperature measurement space connected to the thermocouple air inlet, the thermocouple exhaust hole, and the thermocouple mounting hole.

[0026] The rear end of each composite fairing is stepped and inserted into the mounting hole of each composite measurement component;

[0027] The head of each total pressure sensing head extends into the total pressure measuring space through each total pressure sensing head mounting hole;

[0028] The hot junction of each thermocouple extends into the total temperature measurement space through each thermocouple mounting hole.

[0029] According to at least one embodiment of the present application, in the above-mentioned aircraft engine turbine outlet total temperature and total pressure sensing part measurement installation structure, the total pressure sensing head air inlet on each composite fairing is close to the aircraft engine axis relative to the thermocouple air inlet.

[0030] According to at least one embodiment of the present application, in the above-mentioned aircraft engine turbine outlet total temperature and total pressure sensing portion measurement and installation structure, each total pressure sensing head is a metal circular tube, and the portion of the head facing the airflow is chamfered at an angle of 90°, retaining a sharp edge;

[0031] The air inlet holes of each total pressure sensing head are chamfered at 90°.

[0032] According to at least one embodiment of the present application, in the above-mentioned aircraft engine turbine outlet total temperature and total pressure sensing part measurement and installation structure, the hot junction position of each thermocouple is lower than the thermocouple inlet hole plane and is located at the center of the thermocouple inlet hole;

[0033] Thermocouple air inlet hole is chamfered at 90°.

[0034] According to at least one embodiment of the present application, in the above-mentioned aircraft engine turbine outlet total temperature and total pressure sensing part measurement installation structure, each thermocouple installation hole is stepped;

[0035] Each total temperature and total pressure composite measurement component also includes:

[0036] The thermocouple protection porcelain tube is adjusted on the thermocouple and installed in the thermocouple mounting hole.

[0037] According to at least one embodiment of the present application, in the above-mentioned aircraft engine turbine outlet total temperature and total pressure sensing part measurement and installation structure, the elastic sealing ring has an opening on the ring body, the opening has a width of 0.5 mm and an angle of 117°.

[0038] According to at least one embodiment of the present application, in the above-mentioned aircraft engine turbine outlet total temperature and total pressure sensing part measurement and installation structure, the sealing vibration damping ring has an oblique movable installation seam. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Figure 1 Schematic diagrams of the front and side views of the sensing portion of the sensing portion for measuring the total temperature and total pressure of the turbine outlet of an aircraft engine provided by an embodiment of the present application;

[0040] Figure 2 Schematic diagram of a total temperature and total pressure composite measurement assembly provided in an embodiment of the present application;

[0041] Figure 3 is a schematic diagram of a total pressure sensing head provided in an embodiment of the present application;

[0042] Figure 4 Schematic diagrams of the front view and top view of the composite fairing provided in an embodiment of the present application;

[0043] Figure 5 is a schematic diagram of an external support movable sealing assembly provided in an embodiment of the present application;

[0044] Figure 6 is a schematic diagram of the elastic sealing ring structure provided in an embodiment of the present application;

[0045] Figure 7 is a schematic diagram of a sealing vibration damping ring structure provided in an embodiment of the present application;

[0046] Figure 8 Schematic diagram of the installation structure for measuring the total temperature and total pressure sensing portion of an aircraft engine turbine outlet provided by an embodiment of the present application;

[0047] in:

[0048] 1-Support rod; 2-Total temperature and total pressure composite measurement assembly; 3-Active sealing gasket; 4-External support movable sealing assembly; 5-Inner support sleeve; 6-Pressure nozzle; 7-Adapter seat; 8-Thermocouple connector; 9-External casing; 10-Inner casing;

[0049] 2-1-total pressure sensing head; 2-2-thermocouple; 2-3-composite fairing and 2-4-thermocouple protection porcelain tube;

[0050] 4-1-External support sleeve; 4-2-Sealing seat; 4-3-Elastic sealing ring; 4-4-Sealing pressure plate and 4-5-Split sealing vibration damping ring;

[0051] A-Total pressure sensing head mounting hole; B-Total pressure sensing head air inlet hole; C-Total pressure sensing head exhaust hole; D-Thermocouple mounting hole; E-Thermocouple air inlet hole and F-Thermocouple exhaust hole; J-Active mounting seam.

[0052] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be understood as limiting this application. DETAILED DESCRIPTION

[0053] To make the technical solution and its advantages of the present application clearer, the technical solution of the present application will be described in further detail below in conjunction with the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of the present application and are only used to explain the present application, not to limit the present application. It should be noted that, for ease of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0054] In addition, unless otherwise defined, the technical or scientific terms used in the description of this application should have the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. The words "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer" used in the description of this application are only used to indicate relative directions or positional relationships, and do not imply that the device or component must have a specific orientation, be constructed, or operate in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. Therefore, they should not be understood as limitations on this application. The words "first," "second," "third," and similar terms used in the description of this application are used only for descriptive purposes to distinguish different components and should not be understood to indicate or imply relative importance. The words "one," "an," or "the" used in the description of this application should not be understood as absolute limitations on quantity, but should be understood as meaning the presence of at least one. The words "include" or "comprises" used in the description of this application mean that the element or object listed before the word includes the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0055] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "install", "connect", "connect" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or a connection between two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0056] The following is combined with Figures 1 to 8 This application is described in further detail.

[0057] like Figure 1 As shown, the sensing part for measuring the total temperature and total pressure at the outlet of the aircraft engine turbine mainly consists of a support rod 1, a total temperature and total pressure composite measurement assembly 2, a movable sealing gasket 3, an outer support movable sealing assembly 4, an inner support sleeve 5, a pressure nozzle 6, an adapter seat 7, and a thermocouple connector 8.

[0058] The support rod 1 is the main internal flow channel support and load-bearing component of the sensing part. It is made of high-strength stainless steel or high-temperature resistant alloy material. The interior of the support rod is filled with high-temperature resistant hot cement to fix the internal pressure pipes and thermocouples together.

[0059] The total temperature and total pressure composite measurement assembly 2 is used to measure the total temperature and total pressure flow field parameters. It is installed on the windward front edge of the support rod 1 and is connected to the support rod 1 by welding.

[0060] The movable sealing gasket 3 is an annular movable sealing component, which is inserted into the upper end of the circular boss on the upper part of the support rod 1 and can slide between the support rod 1 and the outer supporting movable sealing component 4.

[0061] The outer support movable sealing assembly 4 is a support and sealing component for the sensed part in the outer casing, and at the same time enables the sensed part to have the ability to adjust and compensate in the circumferential, axial and radial directions of the engine.

[0062] One end of the outer supporting movable sealing assembly 4 is fixed to the mounting seat on the inner casing 10 by means of a threaded connection, and the other end is fixed to the mounting seat on the outer casing 9 by means of a bolt connection.

[0063] The inner support sleeve 5 is connected and supported by the support rod 1 and the adapter seat 7 by welding, and the pressure pipeline and the thermocouple lead of the total temperature and total pressure composite measurement assembly 2 are safely and reliably led out of the outer casing 9.

[0064] The main function of the pressure nozzle 6 is to transmit the pressure parameters measured by the sensing part to the external pressure measuring pipeline, and to be connected to the pressure pipeline of the total temperature and total pressure composite measurement assembly 2 by welding.

[0065] The adapter seat 7 provides support for the pressure nozzle 6 and the thermocouple connector 8, and at the same time distributes the pressure pipeline and thermocouple lead wires led out of the inner support sleeve and connects them to the pressure nozzle 6 and the thermocouple connector 8 respectively.

[0066] The main function of the thermocouple connector 8 is to transfer the thermocouple lead wire of the sensing part to the external temperature data acquisition system.

[0067] The total temperature and total pressure composite measurement assembly 2 mainly measures the total pressure and total temperature parameters of the flow channel in the engine. It consists of a total pressure sensor 2-1, a thermocouple 2-2, a composite fairing 2-3 and a thermocouple protection porcelain tube 2-4. The structure is as follows Figure 2 shown.

[0068] The total pressure sensor 2-1 is a metal tube used to measure the total pressure at the turbine outlet. Figure 3 As shown, the head portion facing the airflow is chamfered at an angle of 90°, burrs are removed, and sharp edges are retained. It is connected to the composite fairing 2-3 by welding, and the total pressure sensing head 2-1 is arranged on the side of the composite fairing 2-3 close to the engine axis.

[0069] Thermocouple 2-2 is a temperature sensing element of the sensing part, which is used to measure the total temperature at the turbine outlet. Its hot junction faces the airflow. After passing through the thermocouple protection porcelain tube 2-4, it is installed together with the stepped mounting hole of the composite fairing 2-3. It is limited and fixed by the hot cement inside the stepped hole and the support rod 1. Thermocouple 2-2 is arranged on the side away from the engine axis.

[0070] The composite fairing 2-3 is a double-pass elliptical cylindrical structure, which is installed in conjunction with the elliptical composite measurement component mounting hole on the windward front edge of the support rod 1 and then welded and fixed. It includes the total pressure head mounting hole A, the total pressure head air inlet hole B, the total pressure head exhaust hole C, the thermocouple mounting hole D, the thermocouple air inlet hole E and the thermocouple exhaust hole F. Figure 4 As shown. The total pressure sensor air inlet B enters the total pressure measurement space, flows through the total pressure sensor 2-1, and exits through the total pressure sensor exhaust C. This structure ensures that the airflow passes through the total pressure sensor 2-1 at a certain internal flow velocity, ensuring that the total pressure sensor 2-1 can accurately measure the total pressure parameters. The 90° chamfer at the total pressure sensor air inlet B increases the angular range of total pressure measurement. The airflow enters the total temperature measurement space through the thermocouple air inlet E, flows through the measuring end of the thermocouple 2-2, and exits through the thermocouple exhaust F. The measuring end is located at the center of the thermocouple air inlet E, with the hot junction positioned below the air inlet plane of the E hole. This structure ensures that the airflow passes through the measuring end of the thermocouple 2-2 at a certain internal flow velocity, reducing the error in the total temperature measurement of the thermocouple 2-2 airflow. The 90° chamfer at the thermocouple air inlet E increases the angular range of total temperature measurement.

[0071] The outer support movable sealing assembly 4 mainly includes an outer support sleeve 4-1, a sealing seat 4-2, an elastic sealing ring 4-3, a sealing pressure plate 4-4 and a sealing vibration damping ring 4-5. Figure 5 shown.

[0072] One end of the outer support sleeve 4-1 is fixed to the mounting seat of the inner casing 10 through an external thread, and the other end is hexagonal with an annular boss structure in the middle. An annular positioning groove is machined in the middle of the annular boss for installing the elastic sealing ring 4-3.

[0073] The elastic sealing ring 4-3 is made of metal material, and the ring body is open so as to be inserted into the annular positioning groove on the annular boss of the outer support sleeve 4-1. The width is 0.5mm and the angle is 117°. Figure 6 shown.

[0074] The outer support sleeve 4-1 and the elastic sealing ring 4-3 are sleeved together and pass through the sealing seat 4-2, and can slide up and down along the axis of the sealing seat 4-2.

[0075] The sealing pressure plate 4-4 is evenly distributed with multiple through holes in the circumferential direction, and the sensing part is connected to the mounting seat of the outer casing 9 by bolt connection, while limiting the movement direction and range of components such as the sealing seat 4-2.

[0076] The sealing vibration damping ring 4-5 is installed between the outer support sleeve 4-1 and the inner support sleeve 5. On the one hand, it can form a soft vibration isolation structure between the outer support sleeve 4-1 and the inner support sleeve 5, reducing the stress fatigue damage that may be caused at the root welding of the inner support sleeve 5 of the long cantilever structure when it vibrates with the aircraft engine. On the other hand, it can seal the high-temperature fuel gas that may penetrate from the interior of the aircraft engine into the space between the outer support sleeve 4-1 and the inner support sleeve 5, reducing the leakage of high-temperature fuel gas.

[0077] The sealing vibration damping ring 4-5 is made of high temperature resistant vibration damping rubber material with J-movable installation seam, which is convenient for installation and replacement. Figure 7 shown.

[0078] The measuring and installation structure of the total temperature and total pressure sensing part of the turbine outlet of an aircraft engine is as follows: Figure 8 As shown, the total temperature and total pressure parameters at the outlet of the engine turbine can be measured simultaneously. The total temperature and total pressure composite measurement component 2 is facing the incoming flow direction. The total pressure sensing head 2-1 senses the total pressure parameters of the flow field, and leads the total pressure through the pressure pipe to the pressure nozzle 6, and is connected to the external pressure sensor through the pressure nozzle to finally obtain the total pressure measurement value. The thermocouple 2-2 senses the total temperature parameters of the flow field. The thermocouple type can be E-type, J-type, N-type, T-type, K-type, R-type and S-type standardized thermocouples. After the lead of the thermocouple 2-2 passes through the support rod 1, the inner support sleeve 5 and the adapter 7, it is connected to the external temperature data acquisition equipment through the thermocouple connector 8 to finally obtain the total temperature measurement value.

[0079] Figure 8 In the middle, the inner compression sealing surface is at point H, the threaded sealing surface is at point I, and the outer sliding sealing surface is at point I. The inner compression sealing surface G is sealed by compressing and deforming the contact plane between the support rod 1 and the inner casing 10 mounting seat to prevent leakage of the inner gas. After the outer support movable seal assembly 4 is screwed into the inner casing 10 mounting seat through threads, the movable sealing gasket 3 is pressed to prevent the inner gas from entering the cavity between the outer support sleeve 4-1 and the inner support sleeve 5 due to the failure of the seal at the inner compression sealing surface G. The threaded sealing surface H is formed by applying sealant when the outer support movable seal assembly 4 is screwed into the inner casing 10 mounting seat to prevent the inner gas from entering the outer casing due to the failure of the seal at the inner compression sealing surface G. The sealing vibration damping ring 4-5 is installed at the outlet position of the cavity between the outer support sleeve 4-1 and the inner support sleeve 5, and adopts an interference fit sealing method to ensure that when the seal at the movable sealing gasket 3 fails, the inner gas will not leak to the outside of the aircraft engine. The sealing seat 4-2 and the elastic sealing ring 4-3 form a sliding seal structure to prevent the leakage of the outer casing air to the outside of the aircraft engine. The outer casing sliding sealing surface I is sealed by the sliding contact between the sealing seat 4-2 and the contact surface of the outer casing 9 mounting seat, thereby preventing the leakage of the outer casing air to the outside of the aircraft engine.

[0080] The temperature of the inner casing 10 and the outer casing 9 of an aircraft engine is different. The temperature of the inner casing 10 is significantly higher than that of the outer casing 9. The thermal expansion of the inner casing 10 and the outer casing 9 is inconsistent. The thermal deformation of the inner casing 10 is significantly greater than that of the outer casing 9. The inner casing 10 will significantly move along the OZ direction and the XY plane relative to the outer casing 9. The sensing part of the design of the present application is connected to the mounting seat of the inner casing 10 and the mounting seat of the outer casing 9 through the outer supporting movable sealing component 4. When the inner casing 10 and the outer casing 9 move in series, the outer supporting sleeve (4-1) will slide along the OZ direction relative to the sealing seat (4-2), and the outer supporting sleeve (4-1) can drive the sealing seat (4-2) to slide in the XY plane relative to the sealing pressure plate (4-4), thereby effectively compensating for the uncoordinated deformation between the inner casing 10 and the outer casing 9 and avoiding damage to the support rod (1).

[0081] In the aforementioned aircraft engine turbine outlet total temperature and total pressure sensing unit measurement and installation structure, the total temperature and total pressure composite measurement assembly 2 is designed to simultaneously perform single-point composite measurement of the total temperature and total pressure parameters in the engine flow field. This highly integrated and compact structure reduces the number of openings in the strut 1, thus avoiding stress concentration and insufficient strength of the strut 1 due to excessive openings. Furthermore, the aforementioned aircraft engine turbine outlet total temperature and total pressure sensing unit measurement and installation structure can be directly inserted and installed from the outside of the engine, offering excellent interchangeability and maintainability, a reliable structure, and improved measurement efficiency. Furthermore, the dual-point mounting structure enhances the static and dynamic strength margins of the sensing unit.

[0082] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to in detail.

[0083] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. A measuring and mounting structure for the total temperature and total pressure sensing portion of an aircraft engine turbine outlet, characterized in that: include: An outer casing (9) having an outer casing measuring hole; The inner casing (10) is arranged in the outer casing (9), and forms an outer casing with the outer casing (9), and its inner casing forms an inner casing, and has an inner casing measuring hole on it; the inner casing measuring hole is stepped; The support rod (1) has a lower end inserted into the inner casing through the inner casing measuring hole, and an upper end thereof has a circular boss; the circular boss is installed in the inner casing measuring hole; Multiple total temperature and total pressure composite measurement components (2) are axially connected to the windward surface of the support rod (1) and are located inside the inner portion, and include a total pressure sensing head (2-1) and a thermocouple (2-2); A movable sealing pad (3) is sleeved on the upper end of the support rod (1); An outer support movable sealing assembly (4) comprises an outer support sleeve (4-1), a sealing seat (4-2), an elastic sealing ring (4-3), a sealing pressure plate (4-4), and a sealing vibration damping ring (4-5), wherein the lower end of the outer support sleeve (4-1) is screwed into the measuring hole of the inner casing to press the movable sealing gasket (3) and the circular boss, the upper end of which extends from the measuring hole of the outer casing and has an annular boss in the middle; the annular boss has an annular positioning groove, in which the elastic sealing ring (4-3) is arranged; the sealing The seat (4-2) is provided with a sealing hole and an annular sealing edge, and is sleeved on the annular boss with the sealing hole; the sealing pressure plate (4-4) is connected to the outer casing (9) by bolts, the sealing pressure plate (4-4) is provided with an annular sealing groove, the annular sealing edge is located in the annular sealing groove, and the radial dimension of the annular sealing edge is smaller than the radial dimension of the annular sealing groove; one end of the sealing vibration damping ring (4-5) extends into the inner portion of one end of the outer support sleeve (4-1) extending out of the outer casing (9), and the other end has an outward annular folded edge; An inner support sleeve (5) has one end that passes through the sealing vibration damping ring (4-5) and extends into the outer support sleeve (4-1), and is connected to the upper end of the support rod (1); An adapter seat (7), one end of which is connected to the other end of the inner support sleeve (5); A plurality of pressure nozzles (6) are connected to the side wall of the adapter seat (7); the pressure pipelines of the respective total pressure sensing heads (2-1) are connected to the respective pressure nozzles (6) through the support rod (1), the inner support sleeve (5), and the interior of the adapter seat (7); A plurality of thermocouple connectors (8) are connected to the other end of the adapter (7); the leads of the respective thermocouples (2-2) are connected to the respective thermocouple connectors (8) through the support rod (1), the inner support sleeve (5), and the interior of the adapter (7); The windward surface of the support rod (1) is provided with a plurality of composite measurement component mounting holes arranged along its axial direction; Each total temperature and total pressure composite measurement assembly (2) further includes: The composite fairing (2-3) has a total pressure sensing head air inlet (B) and a thermocouple air inlet (E) at the front end, a total pressure sensing head exhaust hole (C) and a thermocouple exhaust hole (F) at the side wall, a total pressure sensing head mounting hole (A) and a thermocouple mounting hole (D) at the rear end, and a total pressure measurement space connected to the total pressure sensing head air inlet (B), the total pressure sensing head exhaust hole (C), and the total pressure sensing head mounting hole (A), and a total temperature measurement space connected to the thermocouple air inlet (E), the thermocouple exhaust hole (F), and the thermocouple mounting hole (D); The rear end of each composite fairing (2-3) is stepped and inserted into the mounting hole of each composite measurement component; The head of each total pressure sensing head (2-1) extends into the total pressure measurement space through each total pressure sensing head mounting hole (A); The hot junction of each thermocouple (2-2) extends into the total temperature measurement space through each thermocouple mounting hole (D).

2. The measuring and mounting structure of the sensing part of the total temperature and total pressure of the turbine outlet of an aircraft engine according to claim 1, characterized in that: High-temperature resistant hot cement is potted inside the support rod (1) to fix the pressure pipeline of the total pressure sensing head (2-1) and the leads of each thermocouple (2-2).

3. The measuring and mounting structure of the sensing part of the total temperature and total pressure of the turbine outlet of an aircraft engine according to claim 1, characterized in that: The total pressure sensing head air inlet (B) on each composite fairing (2-3) is closer to the axis of the aircraft engine relative to the thermocouple air inlet (E).

4. The measuring and mounting structure for sensing the total temperature and total pressure at the outlet of an aircraft engine turbine according to claim 1, characterized in that: Each total pressure sensing head (2-1) is a metal circular tube, the head of which is facing the airflow part is chamfered at an angle of 90 degrees, retaining the sharp edge; Each total pressure sensor air inlet hole (B) is chamfered at 90°.

5. The measuring and mounting structure for sensing the total temperature and total pressure at the outlet of an aircraft engine turbine according to claim 1, characterized in that: The hot junction of each thermocouple (2-2) is located below the plane of the thermocouple air inlet (E) and is located at the center of the thermocouple air inlet (E); Thermocouple air inlet hole (E) is chamfered at 90°.

6. The measuring and mounting structure for sensing the total temperature and total pressure at the outlet of an aircraft engine turbine according to claim 1, characterized in that: Each thermocouple mounting hole (D) is stepped; Each total temperature and total pressure composite measurement assembly (2) further includes: Thermocouple protection porcelain tube (2-4) is adjusted on the thermocouple (2-2) and installed in the thermocouple installation hole (D).

7. The measuring and mounting structure for sensing the total temperature and total pressure at the outlet of an aircraft engine turbine according to claim 1, characterized in that: The elastic sealing ring (4-3) has an opening on its ring body, with a width of 0.5 mm and an angle of 117°.

8. The measuring and mounting structure for sensing the total temperature and total pressure at the outlet of an aircraft engine turbine according to claim 1, characterized in that: The sealing vibration damping ring (4-5) is provided with an oblique movable installation seam (J).

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