Gas turbine with telemetry device

Abstract

This invention discloses a gas turbine with a telemetry device. The gas turbine includes a gas turbine rotor, a transmitter, an intermediate shaft, a transmitting antenna, an induction power supply ring, and a stator receiving disk. One end of the gas turbine rotor has a first flange with a mounting cavity. The transmitter is located within the mounting cavity of the first flange. One end of the intermediate shaft has a second flange. The mounting cavity has an opening opposite to the second flange, and the second flange is connected to the first flange. The transmitting antenna and the induction power supply ring are both mounted on the intermediate shaft of the gas turbine and rotate with the intermediate shaft. The stator receiving disk is mounted on the stator component of the gas turbine. The stator receiving disk, the transmitting antenna, and the induction power supply ring are axially spaced opposite to each other along the intermediate shaft. The transmitting antenna and the induction power supply ring are connected to the transmitter. The gas turbine with the telemetry device of this invention has advantages such as simple structure and reasonable configuration.

Description

Technical Field

[0001] This invention relates to the field of gas turbines, and more specifically, to a gas turbine with a telemetry device. Background Technology

[0002] During the development of heavy-duty gas turbines, it is necessary to measure many parameters of the turbine rotor, such as the temperature and strain of the rotor disk and blades, as well as the pressure in the rotating disk cavity. Typically, there are many measurement points. To obtain data from these measurement points, a wireless telemetry system is needed to transmit the data to a ground station.

[0003] In related technologies, the transmitter signal line and power supply line are connected to the transmitting antenna and inductive power supply ring via connectors. The transmitting antenna and inductive power supply ring are integrated into the remote sensing mounting plate structure using bolt fastening, and the whole is inseparable. The stator receiving plate is fixed to the gas turbine cylinder or other stationary components. The receiving antenna and inductive power supply ring are arranged radially or axially opposite to the transmitting antenna and inductive power supply ring to achieve non-contact transmission of signals and electrical energy. This structure is only suitable for operating conditions where the telemetry plate is installed at the end of the rotor and the surrounding space is open, providing conditions for the installation of the stator receiving plate, such as the gas turbine rotor with telemetry function disclosed in patent document CN117927316A, whose telemetry system is arranged at the end of the gas turbine rotor, i.e., the hot end of the gas turbine rotor.

[0004] Heavy-duty gas turbines often employ a cold-end output structure, where the turbine rotor shaft is connected to the generator rotor via a coupling. The shaft end is closed, with components such as the flange and thrust disc located inside the bearing cylinder, leaving extremely limited installation space and making it impossible to install a stator receiving disc. If the telemetry system sensor is placed at the hot end of the rotor, the excessively long lead wire between the sensor and transmitter would significantly increase manufacturing costs. Furthermore, the lead wire is highly susceptible to breakage under high-speed rotor rotation, leading to distorted detection signals and inaccurate measurement results. On the other hand, excessively long lead wires necessitate the creation of lead wire holes or other features on rotor components such as the rotor disc, which could compromise the turbine rotor's strength. Therefore, traditional telemetry layout schemes are unsuitable for this type of heavy-duty gas turbine. Consequently, the wireless telemetry system setup is inappropriate and unsuitable for heavy-duty gas turbine monitoring. Summary of the Invention

[0005] The present invention aims to at least partially solve one of the technical problems in the related art.

[0006] Therefore, embodiments of the present invention propose a gas turbine with a telemetry device that is reasonably configured to detect heavy-duty gas turbines.

[0007] A gas turbine with a telemetry device according to an embodiment of the present invention includes: a gas turbine rotor, one end of which is provided with a first flange, the first flange having a mounting cavity; a transmitter, the transmitter being disposed within the mounting cavity of the first flange; an intermediate shaft, one end of which is provided with a second flange, the mounting cavity having an opening opposite to the second flange, the second flange being connected to the first flange; a transmitting antenna and an inductive power supply ring, and a stator receiving disk, the transmitting antenna and the inductive power supply ring being both disposed on the intermediate shaft of the gas turbine and rotating with the intermediate shaft, the stator receiving disk being disposed on the stator of the gas turbine, the stator receiving disk being axially spaced opposite to the transmitting antenna and the inductive power supply ring along the intermediate shaft, the transmitting antenna and the inductive power supply ring being connected to the transmitter, the transmitting antenna and the inductive power supply ring being used to receive operating parameters transmitted by the transmitter and to transmit the operating parameters to the stator receiving disk, the stator receiving disk being used to transmit the received operating parameters to a ground station.

[0008] In some embodiments, the gas turbine with telemetry device further includes a mounting boss disposed on the outer periphery of the intermediate shaft, and the mounting boss has a mounting groove on the side facing the stator receiving disk, and the transmitting antenna and the inductive power supply ring are disposed in the mounting groove.

[0009] In some embodiments, the gas turbine with telemetry device further includes a remote sensing mounting plate and a sensor. The sensor is disposed on the gas turbine rotor and connected to the transmitter. The sensor is used to detect the operating parameters of the gas turbine rotor. The transmitter is disposed on the remote sensing mounting plate, which is disposed inside the mounting cavity.

[0010] In some embodiments, the gas turbine with telemetry device further includes a first connector assembly and a second connector assembly, one of which is a male connector and the other is a female connector. The first connector assembly is located at the end of the remote sensing mounting plate facing the second flange and is connected to the transmitter. The second connector assembly is located at the end of the second flange facing the transmitter and is connected to the transmitting antenna and the induction power supply ring, so that the first connector assembly and the second connector assembly are connected when the gas turbine rotor and the intermediate shaft are engaged.

[0011] In some embodiments, the intermediate shaft is provided with a mounting hole, the two ends of which are respectively connected to the transmitting antenna, the inductive power supply ring, and the second connector assembly. The gas turbine with a telemetry device also includes a wire, which passes through the mounting hole and is respectively connected to the transmitting antenna, the inductive power supply ring, and the second connector assembly.

[0012] In some embodiments, the intermediate shaft has a cavity extending through the intermediate shaft, and the mounting holes include a first hole, a second hole, and a third hole communicating with each other. The first hole extends radially through the intermediate shaft and one end of the first hole is connected to the transmitting antenna and the inductive power supply ring. The second hole is formed in the cavity and extends axially along the intermediate shaft. The third hole extends from the cavity towards the outside of the cavity and is inclined toward the direction adjacent to the second connector assembly. The third hole is connected to the second connector assembly.

[0013] In some embodiments, the first connector assembly includes a first connector and a second connector, both of which are disposed at one end of the remote sensing mounting plate facing the second flange and are arranged opposite to each other at a radial distance along the second flange. The second connector assembly includes a third connector and a fourth connector, both of which are disposed at one end of the second flange facing the transmitter and are arranged opposite to each other at a radial distance along the second flange.

[0014] In some embodiments, the wire is disposed in the mounting hole by means of skin welding or glue injection.

[0015] In some embodiments, the transmitting antenna and the inductive power supply ring include a ring body, a transmitting antenna body and a first inductive coil. The transmitting antenna body and the first inductive coil are both disposed on the ring body, and the ring body is sleeved on the intermediate shaft and connected to the outer peripheral surface of the intermediate shaft.

[0016] In some embodiments, the stator receiving disk includes a disk body, a receiving antenna, and a second induction coil. The receiving antenna and the second induction coil are both disposed on the disk body, which is disposed on the stator component of the gas turbine. The receiving antenna and the second induction coil are respectively disposed opposite to the transmitting antenna and the first induction coil along the axial distance of the intermediate axis.

[0017] The gas turbine with a telemetry device according to embodiments of the present invention has the following beneficial effects:

[0018] The transmitter, transmitting antenna, induction power supply ring, and stator receiving disk are separated into a modular structure. The transmitter is positioned between the first and second flanges, while the transmitting antenna, induction power supply ring, and stator receiving disk are all located on the outer circumferential surface of the intermediate shaft. This eliminates the need to place the transmitting antenna, induction power supply ring, and stator receiving disk between the gas turbine rotor and the rotor, making the telemetry device suitable for heavy-duty gas turbines with cold-end output and limited shaft end space. This effectively avoids problems such as limited internal rotor space and assembly difficulties, reducing the telemetry device's dependence on the internal space of the rotor shaft system. This allows it to be well-suited for heavy-duty gas turbine models with cold-end output and limited shaft end space, broadening the applicability and scenario adaptability of the telemetry device. At the same time, the modular structure facilitates installation, commissioning, and subsequent maintenance, reduces modifications to the main structure of the gas turbine, and improves overall assembly efficiency and operational reliability. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of a gas turbine with a telemetry device according to an embodiment of the present invention.

[0020] Figure 2 yes Figure 1 A magnified view of part A in the image.

[0021] Figure 3 This is a schematic diagram of the transmitter and remote sensing mounting plate of a gas turbine with a telemetry device according to an embodiment of the present invention.

[0022] Figure 4 This is a schematic diagram of the transmitting antenna and inductive power supply ring of a gas turbine with a telemetry device according to an embodiment of the present invention.

[0023] Figure 5 This is a simplified diagram of a gas turbine with a telemetry device according to an embodiment of the present invention.

[0024] Figure 6 This is an exploded view of the transmitting antenna, inductive power supply ring, mounting boss, and stator receiving disk of a gas turbine with a telemetry device according to an embodiment of the present invention.

[0025] 100. Gas turbines equipped with telemetry devices;

[0026] 1. Gas turbine rotor; 2. Intermediate shaft; 21. Mounting hole; 211. First hole; 212. Second hole; 213. Third hole; 22. Chamber;

[0027] 3. First flange; 4. Second flange; 5. Mounting boss;

[0028] 6. Transmitter;

[0029] 7. Transmitting antenna and inductive power supply loop;

[0030] 8. Stator receiving plate;

[0031] 9. First connector assembly; 91. First connector; 92. Second connector;

[0032] 10. Second connector assembly; 101. Third connector; 102. Fourth connector;

[0033] 11. Static components; 12. Remote sensing installation disk. Detailed Implementation

[0034] A gas turbine with a telemetry device according to an embodiment of the present invention is described below with reference to the accompanying drawings.

[0035] like Figures 1-6 As shown, the gas turbine 100 with a telemetry device according to an embodiment of the present invention includes a gas turbine rotor 1, an intermediate shaft 2, a transmitting antenna, an induction power supply ring 7, and a stator receiving disk 8.

[0036] One end of the gas turbine rotor 1 is provided with a first flange 3, and the first flange 3 has a mounting cavity. The transmitter 6 is located in the mounting cavity of the first flange 3. One end of the intermediate shaft 2 is provided with a second flange 4, and the mounting cavity has an opening opposite to the second flange 4. The second flange 4 is connected to the first flange 3. Specifically, as shown... Figure 1 , Figure 3 and Figure 5 As shown, a first flange 3 is fixedly installed on the left end of the gas turbine rotor 1, and a second flange 4 is fixedly installed on the right end of the intermediate shaft 2. The intermediate shaft 2 and the gas turbine rotor 1 are coaxially connected and fastened through the first flange 3 and the second flange 4. The right end of the intermediate shaft 2 is connected to the generator rotor to transmit the rotational power of the gas turbine rotor 1 to the generator. A mounting cavity is opened on the right end face of the first flange 3 facing the second flange 4. The transmitter 6 is installed inside the mounting cavity through the remote sensing mounting plate 12 to ensure installation reliability and structural stability under high-speed rotation conditions. The gas turbine rotor 1 is equipped with sensors that can collect and monitor multiple key operating parameters of the gas turbine rotor 1 in real time, including but not limited to the temperature and strain of the rotor disk and blades, as well as the internal pressure of the rotating disk cavity. This provides data support for gas turbine operating status monitoring, fault diagnosis, and safety control. The sensors are connected to the transmitter 6, so that the data detected by the sensors is transmitted to the transmitter 6.

[0037] The transmitting antenna and the inductive power supply ring 7 are both mounted on the intermediate shaft 2 of the gas turbine and rotate with the intermediate shaft 2. The stator receiving disk 8 is mounted on the stator component 11 of the gas turbine. The stator receiving disk 8 is axially spaced relative to the transmitting antenna and the inductive power supply ring 7 along the intermediate shaft 2. The transmitting antenna and the inductive power supply ring 7 are connected to the transmitter 6. The transmitting antenna and the inductive power supply ring 7 are used to receive the operating parameters transmitted by the transmitter 6 and transmit the operating parameters to the stator receiving disk 8. The stator receiving disk 8 is used to transmit the received operating parameters to the ground station. Specifically, as shown... Figure 1 , Figure 2 , Figure 5 and Figure 6 As shown, the transmitting antenna and the inductive power supply ring 7 are arranged on the outer circumference of the intermediate shaft 2 and connected to the transmitter 6, and can rotate together with the intermediate shaft 2. The stator receiving disk 8 is installed on the stator component 11 of the gas turbine (such as a fixed structure like the gas turbine casing). The stator receiving disk 8 is arranged with the transmitting antenna and the inductive power supply ring 7 spaced apart from each other on the left and right and opposite to each other. The transmitter 6 transmits the received data to the transmitting antenna and the inductive power supply ring 7. The transmitting antenna and the inductive power supply ring 7 wirelessly transmit the operating parameters detected by the transmitter 6 to the stator receiving disk 8. The stator receiving disk 8 then transmits the received operating parameters to the ground station, thereby realizing non-contact real-time telemetry of the operating parameters of the gas turbine rotor 1.

[0038] The gas turbine 100 with telemetry device provided in this embodiment of the invention adopts a split structure design, independently arranging and functionally separating the transmitter 6, transmitting antenna, and induction power supply ring 7 from the stator receiving disk 8, avoiding interference between components and effectively improving the flexibility and reliability of the structural layout. Specifically, the transmitter 6 is arranged in the assembly space between the first flange 3 and the second flange 4, while the transmitting antenna, induction power supply ring 7, and stator receiving disk 8 are all located on the outer circumferential surface of the intermediate shaft 2. This eliminates the need to arrange the transmitting and receiving components in the narrow space between the gas turbine rotor 1 and the intermediate shaft 2, thus avoiding the problems of limited shaft end space, dense internal structure, and inability to arrange traditional telemetry devices in cold-end output heavy-duty gas turbines. Furthermore, this structural layout significantly reduces the installation space requirements at the end of the gas turbine rotor 1, eliminating the need to confine the telemetry device to the end of the gas turbine rotor 1. This allows the telemetry device to be stably and reliably applied to cold-end output heavy-duty gas turbines with limited shaft end space, significantly improving the applicability and installation adaptability of the telemetry device.

[0039] In some embodiments, the gas turbine 100 with a telemetry device further includes a mounting boss 5, which is disposed on the outer periphery of the intermediate shaft 2. The mounting boss 5 has a mounting groove on the side facing the stator receiver disk 8, and the transmitting antenna and the inductive power supply ring 7 are disposed within the mounting groove. Specifically, as shown... Figure 2 , Figure 5 and Figure 6As shown, the mounting boss 5 is annular and fixedly mounted on the outer periphery of the intermediate shaft 2, allowing it to rotate synchronously with the intermediate shaft 2. A mounting groove is formed on the side of the mounting boss 5 facing the stator receiver disk 8. The transmitting antenna and the inductive power supply ring 7 are reliably mounted in the mounting groove using fasteners to ensure structural stability and installation accuracy under high-speed rotation conditions. The stator receiver disk 8 is correspondingly positioned to the left of the transmitting antenna and the inductive power supply ring 7, arranged axially opposite each other to achieve stable and reliable signal transmission.

[0040] In some embodiments, the gas turbine 100 with telemetry device further includes a remote sensing mounting plate 12 and a sensor (not shown in the figure). The sensor is mounted on the gas turbine rotor 1 and connected to a transmitter 6. The sensor is used to detect the operating parameters of the gas turbine rotor 1. The transmitter 6 is mounted on the remote sensing mounting plate 12, which is disposed within a mounting cavity. Specifically, as... Figure 1 As shown, the sensor can be fixedly mounted on the gas turbine rotor 1 to detect relevant parameters of the gas turbine rotor 1, including but not limited to the temperature and strain of the rotor disk and blades, as well as the internal pressure of the rotating disk cavity. The transmitter 6 is connected to the sensor and can receive and transmit the data collected by the sensor. The remote sensing mounting plate 12 is fixedly mounted in the mounting cavity, and the transmitter 6 is integrated into the remote sensing mounting plate 12, providing reliable mounting support and structural foundation for the transmitter 6.

[0041] In some embodiments, the gas turbine 100 with a telemetry device further includes a first connector assembly 9 and a second connector assembly 10, one of which is a male connector and the other is a female connector. The first connector assembly 9 is located at the end of the remote sensing mounting plate 12 facing the second flange 4 and is connected to the transmitter 6. The second connector assembly 10 is located at the end of the second flange 4 facing the transmitter 6 and is connected to the transmitting antenna and the induction power supply ring 7, so that the first connector assembly 9 and the second connector assembly 10 are connected when the gas turbine rotor 1 and the intermediate shaft 2 are engaged. Specifically, as shown... Figure 1 and Figure 5 As shown, a first connector assembly 9 is provided at the end of the remote sensing mounting plate 12 facing the second flange 4, and a second connector assembly 10 is provided at the end of the second flange 4 facing the first flange 3. The first connector assembly 9 and the second connector assembly 10 can be flexibly configured according to assembly requirements. For example, the first connector assembly 9 can be set as a male connector and the second connector assembly 10 as a female connector, or the second connector assembly 10 can be set as a male connector and the first connector assembly 9 as a female connector.

[0042] When the first flange 3 and the second flange 4 are fastened together by fasteners, the male connector is inserted into the female connector to achieve reliable conduction between the first connector assembly 9 and the second connector assembly 10, thereby completing the transmission of electrical energy to the transmitter 6 and transmitting the operating parameter signals transmitted by the transmitter 6 to the transmitting antenna and the inductive power supply ring 7.

[0043] In some embodiments, the intermediate shaft 2 is provided with a mounting hole 21, the two ends of which are respectively connected to the transmitting antenna and the inductive power supply ring 7 and the second connector assembly 10. The gas turbine 100 with a telemetry device also includes a wire, which passes through the mounting hole 21 and is respectively connected to the transmitting antenna and the inductive power supply ring 7 and the second connector assembly 10. Specifically, as Figure 4 and Figure 5 As shown, mounting hole 21 extends in the left-right direction, with its left and right ends respectively connected to the transmitting antenna, the inductive power supply ring 7, and the second connector assembly 10. The wires include signal transmission lines and power transmission lines. One end of the signal transmission line is connected to the second connector assembly 10, and the second connector assembly 10 and the first connector assembly 9 cooperate to connect the signal transmission line to the signal terminal of the transmitter 6. The other end of the signal transmission line is connected to the corresponding terminals of the transmitting antenna and the inductive power supply ring 7. The power transmission line is made of soft copper wire with an insulating sheath. One end of the power transmission line is connected to the second connector assembly 10, and the second connector assembly 10 and the first connector assembly 9 cooperate to connect the power transmission line to the power circuit of the transmitter 6. The other end of the power transmission line is connected to the corresponding terminals of the transmitting antenna and the inductive power supply ring 7, thereby achieving stable signal and power transmission.

[0044] In some embodiments, the intermediate shaft 2 has a cavity 22 extending through the intermediate shaft 2, and the mounting hole 21 includes a first hole 211, a second hole 212 and a third hole 213 communicating with each other. The first hole 211 extends through the intermediate shaft 2 radially, and one end of the first hole 211 is connected to the transmitting antenna and the inductive power supply ring 7. The second hole 212 is formed in the cavity 22 and extends axially along the intermediate shaft 2. The third hole 213 extends from inside the cavity 22 toward outside the cavity 22 and is inclined toward the direction adjacent to the second connector assembly 10. The third hole 213 is connected to the second connector assembly 10.

[0045] Specifically, such as Figure 1 and Figure 5As shown, the intermediate shaft 2 has a chamber 22 extending in the left-right direction. The mounting hole 21 includes a first hole 211, a second hole 212, and a third hole 213 connected sequentially. The first hole 211 is an inclined hole sloping outwards and to the left, with its left end connected to the transmitting antenna and the inductive power supply ring 7, and its right end connected to the left end of the second hole 212. The second hole 212 is formed on the inner circumferential surface of the chamber 22 and is an axial hole extending in the left-right direction. The third hole 213 is an inclined hole sloping outwards and to the right, with its left end connected to the second hole 212, and its right end formed on the left end face of the second flange 4 and connected to the second connector assembly 10. The wires are sequentially threaded through the first hole 211, the second hole 212, and the third hole 213 to achieve electrical connection between the transmitting antenna and the inductive power supply ring 7 and the second connector assembly 10. Thus, by cooperating with each other, the first hole 211, the second hole 212, and the third hole 213 can effectively avoid the central cavity 22 of the intermediate shaft 2 and the internal rotating parts, preventing interference, wear, or entanglement of the wires during high-speed rotation and improving the reliability of the device operation.

[0046] In some embodiments, the first connector assembly 9 includes a first connector 91 and a second connector 92, both of which are located at the end of the remote sensing mounting plate 12 facing the second flange 4 and are radially spaced relative to each other along the second flange 4. The second connector assembly 10 includes a third connector 101 and a fourth connector 102, both of which are located at the end of the second flange 4 facing the transmitter 6 and are radially spaced relative to each other along the second flange 4. Specifically, as... Figure 1 , Figure 3 and Figure 5 As shown, the first connector 91 and the second connector 92 are installed on the left end face of the remote sensing mounting plate 12 and are arranged opposite each other at intervals in the inward and outward directions. The third connector 101 and the fourth connector 102 are installed on the right end face of the second flange 4 and are also arranged opposite each other at intervals in the inward and outward directions. The first connector 91 and the third connector 101, and the second connector 92 and the fourth connector 102 are respectively arranged opposite each other in the left and right directions. When the first flange 3 and the second flange 4 are fastened together by fasteners, the third connector 101 and the fourth connector 102 are respectively inserted into the first connector 91 and the second connector 92, realizing reliable docking and conduction between the first connector assembly 9 and the second connector assembly 10.

[0047] In some embodiments, the wire is installed in the mounting hole 21 by skin welding or glue injection. Specifically, the skin welding method seals and fixes the gap between the wire and the inner wall of the mounting hole 21 through the skin welding process. The welded layer is tightly attached to the outer circumference of the wire and the wall of the mounting hole 21, which can not only achieve a firm positioning of the wire and prevent the wire from being displaced or worn due to centrifugal force and vibration during high-speed rotation, but also play a good sealing role, preventing external dust, oil, moisture and other impurities from entering the interior of the mounting hole 21, avoiding damage to the wire insulation layer, signal transmission interruption or power supply failure.

[0048] The sealant injection method involves injecting a special sealant with excellent high-temperature resistance, vibration resistance, and insulation properties into the gap between the conductor and the inner wall of the mounting hole 21. After the sealant cures, it forms a tightly sealed and fixed layer that fits the conductor and the mounting hole 21. This not only ensures reliable fixing of the conductor and limits its axial and radial displacement, but also mitigates the impact of vibrations generated during gas turbine operation on the conductor through the buffering effect of the sealant, protecting the conductor and connection parts. It also has excellent insulation, moisture-proof, and corrosion-proof properties, making it suitable for the complex working environment of gas turbines.

[0049] In the actual assembly process, the skin welding or glue sealing method can be flexibly selected according to the specific location of the mounting hole 21, the arrangement of the wires and the actual working conditions. Both fixing methods can effectively solve the problem of fixing the wires in high-speed rotation scenarios, ensure the stability of the wire signal transmission and power transmission, thereby improving the operational reliability and service life of the entire telemetry device, without affecting the structural strength and rotation performance of the intermediate shaft 2.

[0050] In some embodiments, the transmitting antenna and the inductive power supply ring 7 include a ring body, a transmitting antenna body, and a first inductive coil. The transmitting antenna body and the first inductive coil are both disposed on the ring body, and the ring body is sleeved on the intermediate shaft 2 and connected to the outer peripheral surface of the intermediate shaft 2. Specifically, as shown... Figure 4 As shown, the ring body is a circular ring fitted onto the intermediate shaft 2 and fixedly connected to the outer circumference of the intermediate shaft 2. The transmitting antenna body and the first induction coil are both fixed on the ring body, which is fixedly mounted on the mounting boss 5. The transmitting antenna and the induction power supply ring 7 can rotate synchronously with the intermediate shaft 2. The transmitting antenna body and the first induction coil are both connected to the transmitter 6 through wires. Thus, the detection data received by the transmitter 6 can be transmitted to the transmitting antenna and transmitted outward through the wires. The first induction coil generates electrical energy through electromagnetic induction, and the generated electrical energy is transmitted to the transmitter 6 through the wires to provide operating power for the transmitter 6, realizing non-contact induction power supply.

[0051] In some embodiments, the stator receiving disk 8 includes a disk body, a receiving antenna, and a second induction coil. Both the receiving antenna and the second induction coil are disposed on the disk body, which is mounted on the stator component of the gas turbine. The receiving antenna and the second induction coil are respectively positioned axially opposite to the transmitting antenna and the first induction coil along the intermediate shaft 2. Specifically, the disk body is annular and fitted onto the outer periphery of the intermediate shaft 2, with a radial gap between the disk body and the intermediate shaft 2 to avoid rotational interference. The disk body is fixedly mounted on the stator component of the gas turbine, remaining stationary. The receiving antenna and the second induction coil are integrated into a single structure and jointly fixedly mounted on the disk body.

[0052] The receiving antenna and the transmitting antenna are positioned opposite each other at a distance along the left and right direction, and the second induction coil and the first induction coil are positioned opposite each other at a distance along the left and right direction. The second induction coil can be electrically connected to an external power source. When the intermediate shaft 2 drives the first induction coil to rotate, the first induction coil and the second induction coil rotate relative to each other and generate electromagnetic induction, thereby generating induced electrical energy in the first induction coil, providing non-contact inductive power supply for the transmitting antenna, the inductive power supply ring 7, and the transmitter 6.

[0053] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0054] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0055] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between them; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0056] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0057] In this invention, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0058] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A gas turbine with a telemetry device, characterized in that, include: A gas turbine rotor, wherein one end of the gas turbine rotor is provided with a first flange, and the first flange is provided with a mounting cavity; A transmitter, wherein the transmitter is disposed within the mounting cavity of the first flange; An intermediate shaft, one end of which is provided with a second flange, and the mounting cavity has an opening opposite to the second flange, the second flange being connected to the first flange; The system includes a transmitting antenna, an inductive power supply ring, and a stator receiving disk. The transmitting antenna and the inductive power supply ring are both mounted on the intermediate shaft of the gas turbine and rotate with the intermediate shaft. The stator receiving disk is mounted on the stator component of the gas turbine. The stator receiving disk and the transmitting antenna and the inductive power supply ring are arranged opposite to each other along the axial direction of the intermediate shaft. The transmitting antenna and the inductive power supply ring are connected to the transmitter. The transmitting antenna and the inductive power supply ring are used to receive operating parameters transmitted by the transmitter and transmit the operating parameters to the stator receiving disk. The stator receiving disk is used to transmit the received operating parameters to the ground station. The mounting boss is located on the outer periphery of the intermediate shaft, and a mounting groove is provided on the side of the mounting boss facing the stator receiving disk. The transmitting antenna and the inductive power supply ring are located in the mounting groove.

2. The gas turbine with a telemetry device according to claim 1, characterized in that, It also includes a remote sensing mounting plate and a sensor, the sensor being mounted on the gas turbine rotor and connected to the transmitter, the sensor being used to detect the operating parameters of the gas turbine rotor, the transmitter being mounted on the remote sensing mounting plate, and the remote sensing mounting plate being disposed inside the mounting cavity.

3. The gas turbine with a telemetry device according to claim 2, characterized in that, It also includes a first connector assembly and a second connector assembly, one of which is a male connector and the other of which is a female connector. The first connector assembly is located at the end of the remote sensing mounting plate facing the second flange and is connected to the transmitter. The second connector assembly is located at the end of the second flange facing the transmitter and is connected to the transmitting antenna and the induction power supply ring, so that the first connector assembly and the second connector assembly are connected when the gas turbine rotor and the intermediate shaft are engaged.

4. The gas turbine with a telemetry device according to claim 3, characterized in that, The intermediate shaft is provided with a mounting hole, and the two ends of the mounting hole are respectively connected to the transmitting antenna, the inductive power supply ring and the second connector assembly. The gas turbine with telemetry device also includes a wire, which passes through the mounting hole and is respectively connected to the transmitting antenna, the inductive power supply ring and the second connector assembly.

5. The gas turbine with a telemetry device according to claim 4, characterized in that, The intermediate shaft has a cavity extending through it. The mounting holes include a first hole, a second hole, and a third hole that communicate with each other. The first hole extends radially through the intermediate shaft and one end of the first hole is connected to the transmitting antenna and the inductive power supply ring. The second hole is formed in the cavity and extends axially along the intermediate shaft. The third hole extends from the cavity towards the outside of the cavity and is inclined toward the direction adjacent to the second connector assembly. The third hole is connected to the second connector assembly.

6. The gas turbine with a telemetry device according to claim 4, characterized in that, The first connector assembly includes a first connector and a second connector, both of which are located at the end of the remote sensing mounting plate facing the second flange and are radially spaced relative to each other along the second flange. The second connector assembly includes a third connector and a fourth connector, both of which are located at the end of the second flange facing the transmitter and are arranged radially opposite to each other along the second flange.

7. The gas turbine with a telemetry device according to claim 4, characterized in that, The wire is installed in the mounting hole by means of skin welding or glue injection.

8. The gas turbine with a telemetry device according to claim 1, characterized in that, The transmitting antenna and the inductive power supply ring include a ring body, a transmitting antenna body and a first inductive coil. The transmitting antenna body and the first inductive coil are both disposed on the ring body, and the ring body is sleeved on the intermediate shaft and connected to the outer peripheral surface of the intermediate shaft.

9. The gas turbine with a telemetry device according to claim 8, characterized in that, The stator receiving disk includes a disk body, a receiving antenna, and a second induction coil. The receiving antenna and the second induction coil are both disposed on the disk body, which is disposed on the stator component of the gas turbine. The receiving antenna and the second induction coil are respectively disposed opposite to the transmitting antenna and the first induction coil along the axial direction of the intermediate axis.

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