A gas turbine

Abstract

The present application provides a gas turbine, including at least one group of inlet channels, at least two groups of outlet channels, and a connecting channel connecting the inlet channels and the outlet channels on a rotating shaft. At least two foil dynamic pressure bearings are sleeved outside the rotating shaft with a bearing gap between them, and each bearing gap is connected to a group of outlet channels. The compressor is fixedly sleeved on the rotating shaft. The self-static pressure structure is located between two adjacent foil dynamic pressure bearings, and is sleeved outside the rotating shaft with a self-static pressure gap between them, and the self-static pressure gap is connected to the inlet channel. A self-static pressure channel is provided on the self-static pressure structure, one end of which is connected to the self-static pressure gap, and the other end is connected to the air outlet of the compressor; the self-static pressure structure is sealed and connected to two adjacent foil dynamic pressure bearings, so that the two adjacent foil dynamic pressure bearings axially seal the self-static pressure gap. The present application can solve the problem that the gas turbine has many accessories and a large volume, which limits the use scenarios.

Description

Technical Field

[0001] The present application belongs to the field of thermal engines, and specifically relates to a gas turbine. Background Art

[0002] The gas turbine is mainly composed of three parts: compressor, combustion chamber and turbine, and is equipped with intake, exhaust, control, transmission and other auxiliary systems. It uses air as the medium and is a rotary power machine that converts the heat energy generated by fuel combustion into mechanical work for external output. Its working process is as follows: the compressor, which is driven by the turbine and rotates, continuously inhales air from the atmosphere and compresses and increases the pressure. The compressed air enters the combustion chamber, mixes with the injected fuel and burns, becomes high-temperature combustion gas, flows into the turbine to expand and do work, and the pressure of the combustion gas after doing work drops to atmospheric pressure and is finally discharged into the atmosphere. The high-temperature combustion gas formed after combustion and heating has greatly improved its work capacity, making the turbine's work output significantly greater than the compressor's work consumption, and there is more surplus work to output to drive the load.

[0003] Non-contact bearings (such as air bearings) are increasingly used in some high-speed applications due to their low friction coefficient and friction torque, high motion accuracy, and other characteristics. Air bearings rely on the pressure air film in the bearing gap to support the rotor system. Gas bearings can be used in gas turbines. Air bearings require an air source to input air into the bearing gap to produce a pressure air film. Using an air pump to supply air to the air bearing will greatly increase the weight of the gas turbine, which is not conducive to the application of gas turbines in vehicles, drones, and other mobile mechanisms that require lightness, limiting the application of gas turbines. At the same time, traditional air bearings require sealing rings and the like on the bearings for sealing. In high-temperature environments such as near turbines, sealing failure is prone to occur, resulting in reduced operating stability and service life of the air bearing. Therefore, improving the air bearing structure of gas turbines is of great significance for the expansion of gas turbine applications. Summary of the invention

[0004] The purpose of this application is to provide a gas turbine to address the deficiencies in the prior art, so as to solve the technical problem that the gas turbine has many accessories and a large size, which limits its usage scenarios.

[0005] The present application provides a gas turbine, which includes a rotating shaft, at least two foil dynamic pressure bearings, a compressor, a self-static pressure structure and a starter. The rotating shaft is provided with at least one group of inlet channels, at least two groups of outlet channels and a connecting channel connecting the inlet channels with the outlet channels. At least two foil dynamic pressure bearings are sleeved outside the rotating shaft at intervals and have a bearing gap between the foil dynamic pressure bearings and the rotating shaft, and each of the bearing gaps is correspondingly connected to a group of the outlet channels. The compressor is fixedly sleeved on the rotating shaft. The self-static pressure structure is located between two adjacent foil dynamic pressure bearings, and is sleeved outside the rotating shaft at intervals and has a self-static pressure gap between the foil dynamic pressure bearings and the rotating shaft, and the self-static pressure gap is connected to the inlet channel. The self-static pressure structure is provided with a self-static pressure channel, one end of which is connected to the self-static pressure gap, and the other end is connected to the outlet of the compressor; the self-static pressure structure is sealed and connected to the two adjacent foil dynamic pressure bearings.

[0006] Furthermore, the foil dynamic pressure bearing is a radial bearing or a thrust bearing.

[0007] Furthermore, the at least two foil dynamic pressure bearings include two adjacently arranged radial bearings, each of the radial bearings includes a top foil, a wave foil and a bearing sleeve nested in sequence from the inside to the outside, the top foil is spaced apart and sleeved outside the rotating shaft, and the inner surface of the top foil is opposite to the air outlet of the air outlet channel.

[0008] Furthermore, a thrust plate is provided on the rotating shaft, and the air outlet channel has two thrust air outlets, and the two thrust air outlets are respectively opened on the two side surfaces of the thrust plate. The at least two foil dynamic pressure bearings include a radial bearing and a thrust bearing arranged adjacently, and the thrust bearing includes a flat foil and a corrugated foil, and the flat foil is arranged opposite to the thrust air outlet, and the corrugated foil is sleeved between the bearing seat and the flat foil.

[0009] Furthermore, the gas turbine further comprises a bearing seat for mounting the foil dynamic pressure bearing, and the self-static pressure structural member is the bearing seat.

[0010] Furthermore, the air inlet channels are a group, and the group of air inlet channels includes a plurality of air inlet channels arranged in a circumferential array; the connecting channel extends along the axial direction of the rotating shaft, connecting the group of air inlet channels and the at least two groups of air outlet channels.

[0011] Furthermore, there are multiple groups of inlet channels, which are arranged axially, and each group of inlet channels includes multiple inlet channels arranged in a circumferential array. There are multiple connecting channels, and each connecting channel connects one group of inlet channels with at least one group of outlet channels.

[0012] Furthermore, the gas turbine also includes a structural frame and a combustion chamber, the structural frame is formed with an air supply channel and a connecting hole, the air supply channel connects the air outlet of the compressor and the air inlet of the combustion chamber; the structural frame and the self-static pressure structural member cooperate to form a self-static pressure cavity, the self-static pressure cavity is connected to the self-static pressure channel, and the self-static pressure cavity is connected to the air supply channel through the connecting hole.

[0013] Furthermore, a plurality of air-sealing holes are provided on the self-static pressure structure, one end of the air-sealing hole is connected to the self-static pressure channel, and the other end is provided on the inner surface of the self-static pressure structure, the diameter of the air-sealing hole is smaller than the diameter of the self-static pressure channel, and the plurality of air-sealing holes are arranged in a circumferential array along the self-static pressure channel.

[0014] Furthermore, the air intake passage comprises an expansion channel section and an air intake section from the outside to the inside, the radial dimension of the expansion section opening on the outer surface of the rotating shaft is larger than the radial dimension of the air intake section, and the axial dimension of the expansion section opening on the outer surface of the rotating shaft is greater than or equal to the axial dimension of the air intake section. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Other features, objects and advantages of the present application will become more apparent by reading the following detailed description of non-limiting embodiments with reference to the accompanying drawings, in which the same or similar reference numerals represent the same or similar features and the accompanying drawings are not drawn to scale.

[0016] Figure 1 A structural diagram of a gas turbine provided for this application;

[0017] Figure 2 A structural diagram of another gas turbine provided for this application;

[0018] Figure 3 A structural diagram of another gas turbine provided for this application;

[0019] Figure 4 A structural diagram of another gas turbine provided for this application;

[0020] Figure 5 A structural diagram of a foil hydrodynamic bearing provided in this application as a radial bearing;

[0021] Figure 6 A structural diagram of a rotating shaft provided in this application;

[0022] Figure 7 A structural diagram of another rotating shaft provided for this application;

[0023] Figure 8 A matching structure diagram of a rotating shaft and a self-static pressure structural member provided in this application;

[0024] Fig. 9 Another matching structure diagram of a rotating shaft and a self-static pressure structural member provided in this application;

[0025] Fig.10 A diagram of the matching structure of a rotating shaft and a self-static pressure structural member provided in the present application.

[0026] Icons: 100-rotating shaft; 110-intake channel; 120-exhaust channel; 130-connecting channel; 200-foil dynamic pressure bearing; 300-bearing clearance; 400-compressor; 500-self-static pressure structure; 510-self-static pressure clearance; 520-self-static pressure channel; 600-radial bearing seat; 210-radial bearing; 211-top foil 212; 212-wave foil; 213-shaft Sleeve; 140-thrust plate; 141-thrust air outlet; 700-thrust bearing seat; 220-thrust bearing; 800-structural frame; 900-combustion chamber; 810-air supply channel; 820-connecting hole; 830-self-static pressure chamber 830; 530-gas sealing hole; 111-capacity expansion channel section; 112-intake section; 150-first shaft section; 160-second shaft section; 900-starter. DETAILED DESCRIPTION

[0027] The features and exemplary embodiments of various aspects of the present application will be described in detail below. In order to make the purpose, technical solutions and advantages of the present application clearer, the present application will be further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain the present application and are not configured to limit the present application. For those skilled in the art, the present application can be implemented without the need for some of these specific details. The following description of the embodiments is only to provide a better understanding of the present application by illustrating the examples of the present application.

[0028] First, as Figure 1-4As shown, the present application provides a gas turbine, which includes a rotating shaft, at least two foil dynamic pressure bearings 200, a compressor 400, a self-static pressure structure 500 and a starter. The rotating shaft is provided with at least one group of inlet channels 110, at least two groups of outlet channels 120 and a connecting channel 130 connecting the inlet channels 110 and the outlet channels 120. At least two foil dynamic pressure bearings 200 are sleeved outside the rotating shaft at intervals, and there is a bearing gap 300 between the at least two foil dynamic pressure bearings 200 and the rotating shaft, and each of the bearing gaps 300 is correspondingly connected to a group of the outlet channels 120. The compressor 400 is fixedly sleeved on the rotating shaft. The self-static pressure structure 500 is located between two adjacent foil dynamic pressure bearings 200, and is sleeved outside the rotating shaft at intervals, and there is a self-static pressure gap 510 between the at least two foil dynamic pressure bearings 200 and the rotating shaft, and the self-static pressure gap 510 is connected to the inlet channel 110. The self-static pressure structure 500 is provided with a self-static pressure channel 520, one end of which is connected to the self-static pressure gap 510, and the other end of which is connected to the air outlet of the compressor 400. The self-static pressure structure 500 is sealed and connected to the two adjacent foil dynamic pressure bearings 200.

[0029] Optionally, each group of air inlet channels 110 includes a plurality of air inlet channels 110 distributed in an array circumferentially along the axis of the rotating shaft. The self-static pressure structure 500 is also provided with a plurality of self-static pressure channels 520 arranged in an array circumferentially.

[0030] In the above implementation process, when the gas turbine is started, the starter is first used to drive the shaft to rotate. Due to the effect of gravity, the shaft is eccentric to the foil dynamic pressure bearing 200, and there is a wedge-shaped space between the shaft and the foil dynamic pressure bearing 200. During the rotation of the shaft, the surface of the shaft continuously brings the surrounding gas into the wedge-shaped groove, so that a dynamic pressure air film with a certain pressure is formed in the wedge-shaped groove. When the air film pressure is large enough to support the shaft and the load on the shaft, the shaft will be suspended, so that the sliding friction disappears, and the foil dynamic pressure bearing 200 enters the dynamic pressure state to support the shaft. At this time, the compressor 400 also outputs gas stably driven by the shaft. Part of the air output by the compressor 400 enters the combustion chamber 900 for combustion, and the other part of the air enters the self-static pressure channel 520 on the self-static pressure structure 500. Since the self-static pressure structure 500 is sealedly connected to the two adjacent foil dynamic pressure bearings 200, and the foil dynamic pressure bearings 200 are located on both sides of the self-static pressure gap 510, the dynamic pressure air film generated by the foil dynamic pressure bearing 200 can achieve relative axial air sealing of the self-static pressure gap 510, thereby making the self-static pressure gap 510 a relatively sealed space. Therefore, the air in the self-static pressure channel 520 will enter the air inlet channel 110 on the rotating shaft through the self-static pressure gap 510, and then be ejected from the air outlet channel 120 through the connecting channel 130, and then sprayed to the inner surface of the foil dynamic pressure bearing 200, so that the foil dynamic pressure bearing 200 is transformed from the foil dynamic pressure state to the self-static pressure state, thereby supporting the rotating shaft.

[0031] It can be seen that the gas turbine provided in the present application uses the compressor 400 to supply air to the air bearing, so as to omit accessories such as the air pump and the connecting pipe, simplify the structure of the gas turbine, and reduce the weight of the gas turbine. At the same time, the foil dynamic pressure bearing 200 is combined with the air bearing. During the startup phase of the gas turbine, when the air supply of the compressor 400 is insufficient to support the rotating shaft, the foil dynamic pressure bearing 200 is used to support the startup. When the rotating shaft reaches a certain speed, the air supply of the compressor 400 increases, and the foil dynamic pressure bearing 200 is transformed into a self-static air bearing for operation, so as to realize the normal startup of the rotor system.

[0032] Optionally, the preload force of the foil dynamic pressure bearing 200 is reduced so that the starter can rotate the shaft with a smaller force, drive the compressor 400, and then convert it into a self-static pressure air bearing state.

[0033] In a possible implementation, the foil hydrodynamic bearing 200 is a radial bearing 210 or a thrust bearing 220 .

[0034] Optionally, the at least two foil hydrodynamic bearings 200 include two adjacent radial bearings 210; the at least two foil hydrodynamic bearings 200 include adjacent radial bearings 210 and a thrust bearing 220; the at least two foil hydrodynamic bearings 200 include two radial bearings 210 and one thrust bearing 220, and the thrust bearing 220 is located between the two radial bearings 210; the at least two foil hydrodynamic bearings 200 include one radial bearing 210 and two thrust bearings 220, and the radial bearing 210 is located between the two thrust bearings 220.

[0035] Specifically, Figure 5 As shown, the foil dynamic pressure bearing 200 includes a radial bearing 210, and the gas turbine includes a radial bearing seat 600 that is sleeved outside the rotating shaft. The radial bearing 210 includes a top foil 212, a wave foil 212 and a bearing sleeve 213 that are nested in sequence from the inside to the outside, and the bearing sleeve 213 is fixedly connected to the radial bearing seat 600. The top foil 212 is sleeved outside the rotating shaft, and the inner surface of the top foil 212 is opposite to the outlet of the outlet channel 120.

[0036] Specifically, the foil dynamic pressure bearing 200 includes a thrust bearing 220, a thrust plate 140 is arranged on the rotating shaft, and the air outlet channel 120 has two thrust air outlets 141, and the two thrust air outlets 141 are respectively opened on the two side surfaces of the thrust plate 140. The gas turbine also includes a thrust bearing seat 700 sleeved on both sides of the thrust plate 140. The thrust bearing 220 includes a flat foil and a corrugated foil 212, the flat foil is arranged opposite to the thrust air outlet 141, and the corrugated foil 212 is sleeved between the thrust bearing seat 700 and the flat foil.

[0037] In a possible implementation, the gas turbine further includes a bearing seat for mounting the foil hydrodynamic bearing 200 , and the self-hydrostatic structural component 500 is a bearing seat.

[0038] Optionally, the self-static pressure structural member may be the above-mentioned thrust bearing seat, or may be the above-mentioned radial bearing seat.

[0039] In the above embodiment, the original bearing seat of the rotor system of the gas turbine is used as the self-static pressure structural member 500, and the self-static pressure channel 520 is directly opened on the bearing seat, which can effectively simplify the structure of the gas turbine.

[0040] Optionally, the self-static pressure structural member 500 may be a bearing seat, or may be other stator structural members sleeved on the rotating shaft.

[0041] In a possible implementation, Figure 1 , 3As shown in FIG. 4 , the inlet channels 110 are a group, and a group of the inlet channels 110 includes a plurality of inlet channels 110 arranged in a circumferential array. The connecting channel 130 extends along the axial direction of the rotating shaft, connecting the group of inlet channels 110 and the at least two groups of outlet channels 120 .

[0042] In the above implementation process, when the air inlet channels 110 are grouped together, one connecting channel 130 is provided to simultaneously connect one group of air inlet channels 110 with all the air outlet channels 120 .

[0043] In a possible implementation, there are multiple groups of the inlet channels 110, which are arranged axially, and each group of the inlet channels 110 includes multiple inlet channels 110 arranged in a circumferential array. The connecting channel 130 extends along the axial direction of the rotating shaft, connecting the multiple groups of inlet channels 110 and the at least two groups of outlet channels 120.

[0044] Alternatively, if Figure 6 As shown, the rotating shaft includes a first shaft segment 150 and a second shaft segment 160, the first shaft segment 150 has a first end face, the second shaft segment 160 has a second end face, a connecting groove is opened on the first end face of the first shaft segment 150, the first end face and the second end face are welded and connected, and the connecting groove and the second end face cooperate to form the connecting channel 130.

[0045] In a possible implementation, there are multiple groups of the inlet channels 110, which are arranged axially, and each group of the inlet channels 110 includes multiple inlet channels 110 arranged in a circumferential array. There are multiple connecting channels 130, and each connecting channel 130 connects one group of the inlet channels 110 with at least one group of the outlet channels 120.

[0046] When the rotating shaft has two communicating channels 130, the rotating shaft is correspondingly divided into three shaft sections, such as Figure 7 As shown, the dotted line portion is the welding surface of the shaft.

[0047] In a possible embodiment, the gas turbine further includes a structural frame 800 and a combustion chamber 900, wherein the structural frame 800 is formed with an air supply channel 810 and a connecting hole 820, wherein the air supply channel 810 connects the air outlet of the compressor 400 with the air inlet of the combustion chamber 900; a self-static pressure cavity 830 is formed between the structural frame 800 and the self-static pressure structural member 500, wherein the self-static pressure cavity 830 is connected with the self-static pressure channel 520, and the self-static pressure cavity 830 is connected with the air supply channel 810 through the connecting hole 820.

[0048] Specifically, the structural frame 800 may be a suspension component, a connecting component, and various casing structures of a gas turbine.

[0049] In the above implementation process, the gas turbine's original suspension parts, connecting parts, shell structure and other structural frames 800 are used to form the air supply channel 810 and the self-static pressure chamber 830, and a connecting hole 820 is opened on the structural frame 800 to connect the air supply channel 810 and the self-static pressure chamber 830, so that the compressor 400 can inject air into the self-static pressure channel 520.

[0050] In a possible implementation, Figure 8 and 9 As shown, a plurality of air-sealing holes 530 are provided on the self-static pressure structure 500, one end of the air-sealing hole 530 is connected to the self-static pressure channel 520, and the other end is provided on the inner surface of the self-static pressure structure 500, the diameter of the air-sealing hole 530 is smaller than the diameter of the self-static pressure channel 520, and a plurality of the air-sealing holes 530 are arranged in a circumferential array along the self-static pressure channel 520.

[0051] In the above embodiment, the diameter of the air-sealing hole 530 is set smaller than the diameter of the self-static pressure channel 520, so that the pressure of the air ejected from the air-sealing hole 530 is greater than the pressure of the air ejected from the self-static pressure channel 520, and the air-sealing hole 530 is arranged in a circumferential array around the axis of the self-static pressure channel 520 to surround the self-static pressure channel 520, thereby relatively air-sealing the self-static pressure channel 520, so that more air in the self-static pressure channel 520 can enter the air inlet channel 110 of the rotating shaft.

[0052] In a possible implementation, Fig. 9 and 10 As shown, the air intake channel 110 includes an expansion channel section 111 and an air intake section 112 from the outside to the inside. The radial dimension of the expansion section opening on the outer surface of the rotating shaft is larger than the radial dimension of the air intake section 112, and the axial dimension of the expansion section opening on the outer surface of the rotating shaft is greater than or equal to the axial dimension of the air intake section 112.

[0053] In the above implementation process, the expansion channel section 111 is provided to increase the opening area of ​​the air intake channel 110 on the outer surface of the shaft, thereby increasing the air intake amount of the air in the static pressure gap 510 entering the air intake channel 110 .

[0054] In a possible implementation, Fig. 9 and 10 As shown, the cross-sectional area of ​​the expansion channel section 111 gradually decreases from the outside to the inside along the radial direction.

[0055] In the above embodiment, the expansion channel section 111 is funnel-shaped and has an inclined surface, which can encourage the air in the static pressure gap 510 to enter the air intake channel 110 .

[0056] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present application. In addition, features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present application, unless otherwise specified, "multiple" means two or more.

[0057] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it 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, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0058] In the description of the present application, the description with reference to the terms "one embodiment", "some embodiments", "illustrative embodiments", "examples", "specific examples", or "some examples" means that the specific features, structures, materials, or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described may be combined in any one or more embodiments or examples in a suitable manner.

[0059] According to the embodiments described above in the present application, these embodiments do not describe all the details in detail, nor do they limit the present application to the specific embodiments described. Obviously, many modifications and changes can be made based on the above description. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present application, so that those skilled in the art can make good use of the present application and the modifications based on the present application. The present application is limited only by the claims and their full scope and equivalents.

Claims

1. A gas turbine, characterized in that: include: A rotating shaft, on which at least one set of air inlet channels, at least two sets of air outlet channels, and a connecting channel connecting the air inlet channels with the air outlet channels are arranged; At least two foil dynamic pressure bearings are spaced outside the rotating shaft and have a bearing gap between the bearing and the rotating shaft, and each of the bearing gaps is correspondingly connected to a group of the air outlet channels; A compressor, fixedly sleeved on the rotating shaft; A self-static pressure structure is located between two adjacent foil dynamic pressure bearings, and is sleeved outside the rotating shaft at intervals, and has a self-static pressure gap between the self-static pressure gap and the air inlet channel; a self-static pressure channel is opened on the self-static pressure structure, one end of the self-static pressure channel is connected to the self-static pressure gap, and the other end is connected to the air outlet of the compressor; the self-static pressure structure is sealed and connected to the two adjacent foil dynamic pressure bearings; The foil dynamic pressure bearing is a radial bearing or a thrust bearing; The rotating shaft is provided with a thrust plate, the air outlet passage has two thrust air outlets, and the two thrust air outlets are respectively opened on two side surfaces of the thrust plate; The at least two foil dynamic pressure bearings include a radial bearing and a thrust bearing which are arranged adjacent to each other, the thrust bearing includes a flat foil and a corrugated foil, the flat foil is arranged opposite to the thrust air outlet, and the corrugated foil is sleeved between the bearing seat and the flat foil; It also includes a bearing seat for installing the foil dynamic pressure bearing, and the self-static pressure structural member is the bearing seat.

2. A gas turbine according to claim 1, characterized in that: The at least two foil dynamic pressure bearings include two adjacent radial bearings, each of the radial bearings includes a top foil, a wave foil and a bearing sleeve nested in sequence from the inside to the outside, the top foil is spaced apart outside the rotating shaft, and the inner surface of the top foil is opposite to the air outlet of the air outlet channel.

3. A gas turbine according to claim 1, characterized in that: The air inlet channels are a group, and the group of air inlet channels includes a plurality of air inlet channels arranged in a circumferential array; the connecting channel extends along the axial direction of the rotating shaft, connecting the group of air inlet channels and the at least two groups of air outlet channels.

4. A gas turbine according to claim 1, characterized in that: There are multiple groups of air inlet channels, which are arranged axially, and each group of air inlet channels includes multiple air inlet channels arranged in a circumferential array; There are a plurality of communicating channels, and each communicating channel communicates with a group of the air inlet channels and at least one group of the air outlet channels.

5. A gas turbine according to claim 1, characterized in that: It also includes a structural frame and a combustion chamber, the structural frame is formed with an air supply channel and a connecting hole, the air supply channel connects the air outlet of the compressor and the air inlet of the combustion chamber; the structural frame and the self-static pressure structural member cooperate to form a self-static pressure cavity, the self-static pressure cavity is connected to the self-static pressure channel, and the self-static pressure cavity is connected to the air supply channel through the connecting hole.

6. A gas turbine according to claim 1, characterized in that: A plurality of air-sealing holes are provided on the self-static pressure structure, one end of the air-sealing hole is connected to the self-static pressure channel, and the other end is provided on the inner surface of the self-static pressure structure, the diameter of the air-sealing hole is smaller than the diameter of the self-static pressure channel, and the plurality of air-sealing holes are arranged in a circumferential array along the self-static pressure channel.

7. The gas turbine according to claim 1, characterized in that The air intake passage comprises an expansion channel section and an air intake section from outside to inside, the radial dimension of the expansion channel section opening on the outer surface of the rotating shaft is larger than the radial dimension of the air intake section, and the axial dimension of the expansion channel section opening on the outer surface of the rotating shaft is larger than or equal to the axial dimension of the air intake section.

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