CN115773182A - Gas turbine - Google Patents

Abstract

The application provides a gas turbine, be provided with at least a set of inlet channel, at least two sets of outlet channel and intercommunication inlet channel and outlet channel's intercommunication passageway in the pivot. At least two foil dynamic pressure bearings are sleeved outside the rotating shaft at intervals, bearing gaps are formed between the foil dynamic pressure bearings and the rotating shaft, and each bearing gap is correspondingly communicated with one group of air outlet channels. The compressor is fixedly sleeved on the rotating shaft. The self-static pressure structural part is positioned between two adjacent foil dynamic pressure bearings, is sleeved outside the rotating shaft at intervals, has a self-static pressure gap with the rotating shaft, and is communicated with the air inlet channel. A self-static pressure channel is formed in the self-static pressure structural member, one end of the self-static pressure channel is communicated with the self-static pressure gap, and the other end of the self-static pressure channel is communicated with an air outlet of the air compressor; the self-static pressure structural part is hermetically connected with the two adjacent foil dynamic pressure bearings so that the two adjacent foil dynamic pressure bearings perform axial air sealing on the self-static pressure gap. The application can solve the problem that the use scene is limited due to multiple accessories and large volume of the gas turbine.

Description

Gas turbine

Technical Field

The application belongs to the heat engine field, concretely relates to gas turbine.

Background

The gas turbine mainly comprises three parts of a gas compressor, a combustion chamber and a turbine, is matched with an air inlet system, an air exhaust system, a control system, a transmission system and other auxiliary systems, takes air as a medium, and is a rotary power machine which converts heat energy generated by fuel combustion into mechanical work and outputs the mechanical work. The working process is as follows: the compressor driven by the turbine to rotate continuously sucks air from the atmosphere and compresses and boosts the air, the compressed air enters the combustion chamber and is mixed and combusted with the injected fuel to become high-temperature gas, the high-temperature gas flows into the turbine to expand and do work, and the pressure of the gas after doing work is reduced to the atmospheric pressure and is finally discharged into the atmosphere. The high-temperature gas formed after combustion heating and temperature rise has greatly improved work-doing capability, so that the work output of the turbine is obviously greater than the power consumption of the gas compressor, and more surplus work is output externally to drive the load.

Non-contact bearings (such as air bearings) are increasingly used in high-speed occasions due to the characteristics of small friction coefficient and friction torque, high movement precision and the like. The air bearing relies on a pressurized air film in the bearing gap to support the rotor system. Gas bearings are applicable to gas turbines. Air bearing needs the air supply to input the air and then produce the pressure air film in to the bearing clearance, adopts the air pump to carry out the air feed to air bearing and can greatly increase gas turbine's weight, is unfavorable for gas turbine to be applied to vehicle, unmanned aerial vehicle etc. and requires light moving mechanism, has restricted gas turbine's application scenario. Meanwhile, a sealing ring and the like are required to seal a bearing of the traditional air bearing, and the condition of sealing failure is easy to occur under high-temperature environments such as the vicinity of a turbine and the like, so that the operation stability and the service life of the air bearing are reduced. Therefore, the improvement of the air bearing structure of the gas turbine has great significance for the expansion of the application occasions of the gas turbine.

Disclosure of Invention

The application aims to provide a gas turbine aiming at overcoming the defects in the prior art so as to solve the technical problem that the use scene is limited due to the fact that the gas turbine has many accessories and is large in size.

The application provides a gas turbine, which comprises a rotating shaft, at least two foil dynamic pressure bearings, a gas compressor, a self-static pressure structural part and a starter. The rotating shaft is provided with at least one group of air inlet channels, at least two groups of air outlet channels and a communication channel for communicating the air inlet channels with the air outlet channels. And the foil dynamic pressure bearings are sleeved outside the rotating shaft at intervals, a bearing gap is formed between the foil dynamic pressure bearings and the rotating shaft, and each bearing gap is correspondingly communicated with one group of the air outlet channels. The compressor is fixedly sleeved on the rotating shaft. The self-static pressure structural part is positioned between two adjacent foil dynamic pressure bearings, is sleeved outside the rotating shaft at intervals, and is provided with a self-static pressure gap between the rotating shaft, and the self-static pressure gap is communicated with the air inlet channel. A self-static pressure channel is formed in the self-static pressure structural member, one end of the self-static pressure channel is communicated with the self-static pressure gap, and the other end of the self-static pressure channel is communicated with an air outlet of the air compressor; and the self-static pressure structural part is hermetically connected with two adjacent foil dynamic pressure bearings.

Further, the foil dynamic pressure bearing is a radial bearing or a thrust bearing.

Further, the at least two foil dynamic pressure bearings comprise two radial bearings which are adjacently arranged, each radial bearing comprises a top foil, a corrugated foil and a bearing sleeve which are sequentially nested from inside to outside, the top foil is arranged outside the rotating shaft in a sleeved mode, and the inner surface of the top foil is opposite to the air outlet of the air outlet channel.

Furthermore, a thrust disc is arranged on the rotating shaft, the air outlet channel is provided with two thrust air outlets, and the two thrust air outlets are respectively arranged on two side faces of the thrust disc. The two foil dynamic pressure bearings comprise a radial bearing and a thrust bearing which are arranged adjacently, the thrust bearing comprises a flat foil and a wave foil, the flat foil is arranged opposite to the thrust air outlet, and the wave foil is sleeved between the bearing seat and the flat foil.

Further, the gas turbine also comprises a bearing seat for mounting the foil dynamic pressure bearing, and the self-static pressure structural part is the bearing seat.

Further, the air inlet passages are in one group, and the air inlet passages in one group comprise a plurality of air inlet passages arranged in a circumferential array; the communicating channel extends along the axial direction of the rotating shaft and communicates the group of air inlet channels and the at least two groups of air outlet channels.

Furthermore, the air inlet channels are provided with a plurality of groups, the air inlet channels are arranged along the axial direction, and each air inlet channel comprises a plurality of air inlet channels arranged in a circumferential array. The communication channel is a plurality of, and every communication channel intercommunication a set of inlet channel and at least a set of outlet channel.

Further, the gas turbine also comprises a structural frame and a combustion chamber, wherein the structural frame is provided with a gas supply channel and a communicating hole, and the gas supply channel is communicated with the gas outlet of the gas compressor and the gas inlet of the combustion chamber; the structure frame is matched with the self-static pressure structural part to form a self-static pressure cavity, the self-static pressure cavity is communicated with the self-static pressure channel, and the self-static pressure cavity is communicated with the gas supply channel through the communication hole.

Furthermore, a plurality of air sealing holes are formed in the self-static pressure structural part, one end of each air sealing hole is communicated with the self-static pressure channel, the other end of each air sealing hole is formed in the inner surface of the self-static pressure structural part, the diameter of each air sealing hole is smaller than that of the self-static pressure channel, and the air sealing holes are circumferentially arrayed along the self-static pressure channel.

Furthermore, the inlet channel is by outer to interior dilatation passageway section and the section of admitting air of including, the dilatation section is in pivot surface open-ended radial dimension is greater than the radial dimension of the section of admitting air, the dilatation section is in pivot surface open-ended axial dimension more than or equal to the axial dimension of the section of admitting air.

Drawings

Other features, objects, and advantages of the present application will become apparent from the following detailed description of non-limiting embodiments thereof, when read in conjunction with the accompanying drawings, in which like reference characters designate the same or similar parts throughout the figures thereof, and which are not to scale.

FIG. 1 is a block diagram of a gas turbine provided herein;

FIG. 2 is a block diagram of another gas turbine engine provided herein;

FIG. 3 is a block diagram of yet another gas turbine engine provided herein;

FIG. 4 is a block diagram of yet another gas turbine provided herein;

FIG. 5 is a block diagram of a foil hydrodynamic bearing as a journal bearing according to the present application;

FIG. 6 is a structural view of a spindle provided herein;

FIG. 7 is a block diagram of another spindle provided in the present application;

FIG. 8 is a structural diagram of a rotating shaft and a self-static pressure structural member according to the present disclosure;

FIG. 9 is a schematic view of another embodiment of the present disclosure;

fig. 10 is a structural view of a combination of a rotating shaft and a self-static pressure structural member according to another embodiment of the present disclosure.

An icon: 100-a rotating shaft; 110-an intake passage; 120-an outlet channel; 130-a communication channel; 200-foil hydrodynamic bearings; 300-bearing clearance; 400-an air compressor; 500-self-hydrostatic structural members; 510-self-static pressure gap; 520-self-hydrostatic channel; 600-radial bearing seats; 210-a radial bearing; 211-top foil 212; 212-bump foil; 213-a bearing sleeve; 140-a thrust disc; 141-thrust air outlet; 700-thrust bearing seat; 220-a thrust bearing; 800-structural frame; 900-a combustion chamber; 810-gas supply channel; 820-a communication hole; 830-self hydrostatic chamber 830; 530-sealing holes; 111-capacity expansion channel section; 112-an air intake section; 150-a first shaft section; 160-a second shaft section; 900-starter.

Detailed Description

Features and exemplary embodiments of various aspects of the present application will be described in detail below, and in order to make objects, technical solutions and advantages of the present application more apparent, the present application will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application. It will be apparent to one skilled in the art that the present application may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the present application by illustrating examples thereof.

In a first aspect, as shown in fig. 1-4, the present application provides a gas turbine comprising a shaft, at least two foil dynamic pressure bearings 200, a compressor 400, a self-static pressure structure 500, and a starter motor. The rotating shaft is provided with at least one group of air inlet channels 110, at least two groups of air outlet channels 120 and a communication channel 130 for communicating the air inlet channels 110 and the air outlet channels 120. At least two foil dynamic pressure bearings 200 are sleeved outside the rotating shaft at intervals, a bearing gap 300 is arranged between each foil dynamic pressure bearing and the rotating shaft, and each bearing gap 300 is correspondingly communicated with one group of air outlet channels 120. The compressor 400 is fixedly sleeved on the rotating shaft. And the self-static pressure structural part 500 is positioned between two adjacent foil dynamic pressure bearings 200, is sleeved outside the rotating shaft at intervals, and is provided with a self-static pressure gap 510 between the rotating shaft, wherein the self-static pressure gap 510 is communicated with the air inlet channel 110. The self-static pressure structural member 500 is provided with a self-static pressure channel 520, one end of the self-static pressure channel 520 is communicated with the self-static pressure gap 510, and the other end is communicated with the air outlet of the compressor 400. The self-static pressure structural member 500 is hermetically connected with two adjacent foil dynamic pressure bearings 200

Optionally, each set of air inlet passages 110 includes a plurality of air inlet passages 110 circumferentially arrayed along the axial center of the rotating shaft. Self-static pressure structure 500 also has a plurality of self-static pressure channels 520 formed therein in a circumferential array.

In the implementation process, when the gas turbine is started, the starter is firstly adopted to drive the rotating shaft to rotate, due to the action of gravity, the rotating shaft and the foil dynamic pressure bearing 200 are eccentric, a wedge-shaped space exists between the rotating shaft and the foil dynamic pressure bearing 200, in the rotating motion process of the rotating shaft, surrounding gas is continuously brought into the surface of the rotating shaft to enter the wedge-shaped groove, so that a dynamic pressure gas film with certain pressure is formed in the wedge-shaped groove, when the pressure of the gas film is large enough to support the rotating shaft and the load on the rotating shaft, the rotating shaft can suspend, so that the sliding friction force disappears, the foil dynamic pressure bearing 200 enters a dynamic pressure state, and the support of the rotating shaft is realized. At this time, the compressor 400 is also driven by the rotating shaft to stably output air, a 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 structural member 500. Since the auto-static pressure structure 500 is hermetically connected to two adjacent foil dynamic pressure bearings 200, and the foil dynamic pressure bearings 200 are located at two sides of the auto-static pressure gap 510, the dynamic pressure films generated by the foil dynamic pressure bearings 200 can achieve a relative axial air seal to the auto-static pressure gap 510, so that the auto-static pressure gap 510 becomes a relatively sealed space. Therefore, air in the self-static pressure channel 520 enters the air inlet channel 110 on the rotating shaft through the self-static pressure gap 510, is ejected from the air outlet channel 120 through the communication channel 130, and is ejected to the inner surface of the foil hydrodynamic bearing 200, so that the foil hydrodynamic bearing 200 is converted from a foil hydrodynamic state to a self-static pressure state, and the rotating shaft is supported.

Therefore, the gas turbine provided by the application adopts the gas compressor 400 to supply gas for the air bearing, so that accessories such as a gas pump and a connecting pipe are omitted, the structure of the gas turbine is simplified, and the weight of the gas turbine is reduced. Meanwhile, the foil hydrodynamic bearing 200 is combined with an air bearing, and the foil hydrodynamic bearing 200 is used for supporting and starting when the air supply of the air compressor 400 is insufficient to support the rotating shaft in the starting stage of the gas turbine. When the rotating shaft reaches a certain rotating speed, the air supply of the air compressor 400 is increased, the foil dynamic pressure bearing 200 is changed into a self-static pressure air bearing to operate, and the normal start of the rotor system is realized.

Alternatively, the pre-tightening force of the foil hydrodynamic bearing 200 is reduced, so that the starter can rotate the rotating shaft with a small force to drive the compressor 400, and then the state is converted into the self-static pressure air bearing state.

In one possible embodiment, the foil hydrodynamic bearing 200 is a radial bearing 210 or a thrust bearing 220.

Alternatively, the at least two foil hydrodynamic bearings 200 comprise two adjacent radial bearings 210; the at least two foil hydrodynamic bearings 200 include adjacent radial bearings 210 and thrust bearings 220; the at least two foil hydrodynamic bearings 200 include two radial bearings 210 and a thrust bearing 220, the thrust bearing 220 being located between the two radial bearings 210; the at least two foil hydrodynamic bearings 200 include a radial bearing 210 and two thrust bearings 220, and the radial bearing 210 is located at the two thrust bearings 220.

Specifically, as shown in fig. 5, the foil hydrodynamic bearing 200 includes a radial bearing 210, and the gas turbine includes a radial bearing seat 600 spaced around the shaft. Radial bearing 210 includes top foil 212, ripples foil 212 and bearing housing 213 of nesting in proper order from inside to outside, bearing housing 213 and radial bearing frame 600 fixed connection, top foil 212 interval cover is established outside the pivot, the internal surface of top foil 212 with outlet channel 120's gas outlet is relative.

Specifically, the foil hydrodynamic bearing 200 includes a thrust bearing 220, the rotating shaft is provided with a thrust disc 140, the air outlet channel 120 has two thrust air outlets 141, and the two thrust air outlets 141 are respectively arranged on two side surfaces of the thrust disc 140. The gas turbine further includes thrust bearing blocks 700 spaced on opposite sides of the thrust disk 140. The thrust bearing 220 includes a flat foil and a bump foil 212, the flat foil is disposed opposite to the thrust air outlet 141, and the bump foil 212 is sleeved between the thrust bearing seat 700 and the flat foil.

In a possible embodiment, the gas turbine further comprises a bearing seat for mounting the foil dynamic pressure bearing 200, and the self-static pressure structure 500 is the bearing seat.

Alternatively, the self-static pressure structural member may be the thrust bearing seat or the radial bearing seat.

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 formed on the bearing seat, so that the structure of the gas turbine can be effectively simplified.

Alternatively, the self-static pressure structure 500 may be a bearing seat, or may be another stator structure component sleeved on the rotating shaft.

In one possible embodiment, as shown in fig. 1, 3 and 4, the intake passages 110 are in a group, and a group of the intake passages 110 includes a plurality of intake passages 110 arranged in a circumferential array. The communication channel 130 extends along the axial direction of the rotating shaft and communicates the set of inlet channels 110 and the at least two sets of outlet channels 120.

In the above implementation, when the inlet channels 110 are in a group, one communication channel 130 is provided to communicate one group of inlet channels 110 with all outlet channels 120 at the same time.

In one possible embodiment, there are multiple sets of the intake passages 110, the multiple sets of the intake passages 110 are arranged along the axial direction, and each set of the intake passages 110 includes multiple intake passages 110 arranged in a circumferential array. The communication channel 130 extends along the axial direction of the rotating shaft and communicates the plurality of sets of inlet channels 110 and the at least two sets of outlet channels 120.

Optionally, as shown in fig. 6, the rotating shaft includes a first shaft section 150 and a second shaft section 160, the first shaft section 150 has a first end surface, the second shaft section 160 has a second end surface, a communication groove is opened on the first end surface of the first shaft section 150, the first end surface and the second end surface are welded and connected, and the communication groove and the second end surface cooperate to form the communication channel 130.

In one possible embodiment, there are multiple sets of the intake passages 110, the multiple sets of the intake passages 110 are arranged along the axial direction, and each set of the intake passages 110 includes multiple intake passages 110 arranged in a circumferential array. The number of the communication channels 130 is plural, and each of the communication channels 130 communicates one set of the inlet channels 110 with at least one set of the outlet channels 120.

When the shaft has two communicating channels 130, the shaft is divided into three shaft segments, as shown in fig. 7, and the dotted line portion is the welding surface of the shaft.

In a possible embodiment, the gas turbine further includes a structural frame 800 and a combustion chamber 900, the structural frame 800 is formed with a gas supply channel 810 and a communication hole 820, the gas supply channel 810 communicates the outlet of the compressor 400 with the 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 in a matching manner, the self-static pressure cavity 830 is communicated with the self-static pressure channel 520, and the self-static pressure cavity 830 is communicated with the gas supply channel 810 through the communication hole 820.

Specifically, the structural frame 800 may be a gas turbine suspension, connection, and various housing structures.

In the implementation process, the gas supply channel 810 and the self-static pressure cavity 830 are formed by the structural frame 800 such as the original suspension part, the original connecting part, the original shell structure and the like of the gas turbine, and the communication hole 820 is formed in the structural frame 800 and is communicated with the gas supply channel 810 and the self-static pressure cavity 830, so that the gas compressor 400 injects gas into the self-static pressure channel 520.

In one possible embodiment, as shown in fig. 8 and 9, a plurality of air sealing holes 530 are opened on the self-static pressure structural member 500, one end of each air sealing hole 530 is communicated with the self-static pressure channel 520, the other end of each air sealing hole 530 is opened on the inner surface of the self-static pressure structural member 500, the diameter of each air sealing hole 530 is smaller than that of the self-static pressure channel 520, and the air sealing holes 530 are circumferentially arranged in an array along the self-static pressure channel 520.

In the above embodiment, the diameter of the air seal holes 530 is set smaller than the diameter of the self-static pressure passage 520, so that the pressure of the air ejected from the air seal holes 530 is greater than the pressure of the air ejected from the self-static pressure passage 520, and the air seal holes are arranged in a circumferential array around the axis of the self-static pressure passage 520 so as to surround the self-static pressure passage 520, thereby relatively air-sealing the self-static pressure passage 520, so that more air from the self-static pressure passage 520 can enter the air intake passage 110 of the spindle.

In a possible embodiment, as shown in fig. 9 and 10, the air inlet channel 110 includes, from outside to inside, an expansion channel section 111 and an air inlet section 112, a radial size of an opening of the expansion section on the outer surface of the rotating shaft is greater than a radial size of the air inlet section 112, and an axial size of the opening of the expansion section on the outer surface of the rotating shaft is greater than or equal to an axial size of the air inlet section 112.

In the above implementation process, the expansion channel section 111 is provided to increase the opening area of the intake channel 110 on the outer surface of the rotating shaft, so as to increase the intake amount of the air entering the intake channel 110 from the static pressure gap 510.

In one possible embodiment, as shown in fig. 9 and 10, the cross-sectional area of the expansion channel section 111 is gradually reduced from the outside to the inside in the radial direction.

In the above embodiment, the expansion passage section 111 is formed in a funnel shape, and an inclined surface is provided to urge the air from the static pressure gap 510 into the intake passage 110.

In the description of the present application, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the present application and to simplify the description, but are not intended to indicate or imply that the device or element so referred to must have a particular orientation, be constructed in a particular orientation, and be operated in a particular manner, and are not to be construed as limiting the present application. Furthermore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, "a plurality" means two or more unless otherwise specified.

In the description of the present application, it should be noted that, unless otherwise explicitly stated or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, a fixed connection, a detachable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.

In the description of the present application, reference to the description of the terms "one embodiment," "some embodiments," "an illustrative embodiment," "an example," "a specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present application. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

In accordance with the embodiments of the present application as described above, these embodiments are not exhaustive and do not limit the application to the specific embodiments described. Obviously, many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the application and its practical application, to thereby enable others skilled in the art to best utilize the application and its various modifications as are suited to the particular use contemplated. The application is limited only by the claims and their full scope and equivalents.

Claims (10)

1. A gas turbine engine, comprising:

the rotating shaft is provided with at least one group of air inlet channels, at least two groups of air outlet channels and a communication channel for communicating the air inlet channels and the air outlet channels;

at least two foil dynamic pressure bearings are sleeved outside the rotating shaft at intervals, bearing gaps are formed between the bearings and the rotating shaft, and each bearing gap is correspondingly communicated with one group of air outlet channels;

the compressor is fixedly sleeved on the rotating shaft;

the self-static pressure structural part is positioned between two adjacent foil dynamic pressure bearings, is sleeved outside the rotating shaft at intervals, has a self-static pressure gap with the rotating shaft, and is communicated with the air inlet channel; a self-static pressure channel is formed in the self-static pressure structural member, one end of the self-static pressure channel is communicated with the self-static pressure gap, and the other end of the self-static pressure channel is communicated with an air outlet of the air compressor; and the self-static pressure structural part is hermetically connected with two adjacent foil dynamic pressure bearings.

2. A gas turbine according to claim 1, wherein said foil hydrodynamic bearing is a radial bearing or a thrust bearing.

3. The gas turbine according to claim 2, wherein the at least two foil dynamic pressure bearings comprise two adjacently arranged radial bearings, each radial bearing comprises a top foil, a corrugated foil and a bearing sleeve which are sequentially nested from inside to outside, the top foil spacer sleeve is arranged outside the rotating shaft, and the inner surface of the top foil is opposite to the air outlet of the air outlet channel.

4. The gas turbine according to claim 2, wherein a thrust disc is provided on the rotating shaft, and the air outlet channel has two thrust air outlets respectively provided on both side surfaces of the thrust disc;

the two foil dynamic pressure bearings comprise a radial bearing and a thrust bearing which are arranged adjacently, the thrust bearing comprises a flat foil and a wave foil, the flat foil is arranged opposite to the thrust air outlet, and the wave foil is sleeved between the bearing seat and the flat foil.

5. A gas turbine according to any one of claims 1 to 4, further comprising a bearing housing for mounting said foil dynamic pressure bearing, said self-hydrostatic structure being said bearing housing.

6. A gas turbine according to any one of claims 1 to 4, wherein said inlet passages are in a group, a group of said inlet passages comprising a plurality of inlet passages arranged in a circumferential array; the communication channel extends along the axial direction of the rotating shaft and is communicated with the group of air inlet channels and the at least two groups of air outlet channels.

7. A gas turbine according to any one of claims 1 to 4, wherein there are a plurality of said inlet passages, the plurality of said inlet passages being axially aligned, each said inlet passage comprising a plurality of inlet passages arranged in a circumferential array;

the communication channel is a plurality of, and every communication channel intercommunication a set of inlet channel and at least a set of outlet channel.

8. The gas turbine according to any one of claims 1 to 4, further comprising a structural frame and a combustion chamber, the structural frame being formed with a gas supply passage and a communication hole, the gas supply passage communicating an outlet of the compressor with an inlet of the combustion chamber; the structure frame is matched with the self-static pressure structural part to form a self-static pressure cavity, the self-static pressure cavity is communicated with the self-static pressure channel, and the self-static pressure cavity is communicated with the gas supply channel through the communication hole.

9. The gas turbine according to any one of claims 1 to 4, wherein a plurality of air sealing holes are formed in the self-static pressure structural member, one end of each air sealing hole is communicated with the self-static pressure passage, the other end of each air sealing hole is formed in the inner surface of the self-static pressure structural member, the diameter of each air sealing hole is smaller than that of the self-static pressure passage, and the plurality of air sealing holes are arranged in a circumferential array along the self-static pressure passage.

10. The gas turbine according to any one of claims 1 to 4, wherein the intake passage includes, from outside to inside, a capacity expansion passage section and an intake section, a radial dimension of an opening of the capacity expansion section in the outer surface of the rotating shaft is larger than a radial dimension of the intake section, and an axial dimension of the opening of the capacity expansion section in the outer surface of the rotating shaft is larger than or equal to an axial dimension of the intake section.

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