CN115324730A

CN115324730A - Rotor system and gas turbine

Info

Publication number: CN115324730A
Application number: CN202210983582.4A
Authority: CN
Inventors: 段萌珠
Original assignee: Xingchen Mengxiang Technology Beijing Co ltd
Current assignee: Xingchen Mengxiang Technology Beijing Co ltd
Priority date: 2022-08-16
Filing date: 2022-08-16
Publication date: 2022-11-11

Abstract

The invention discloses a rotor system, which comprises a rotating shaft, a gas compressor, a turbine and an inner air bearing, wherein the gas compressor and the turbine are sequentially arranged on the rotating shaft in the axial direction; a shaft connecting through hole is formed in the position, corresponding to the turbine, of the rotating shaft, and an in-shaft bearing cavity is formed in at least one axial end of the rotating shaft; the part of the inner air bearing extending into the shaft inner bearing cavity and the circumferential inner wall of the shaft inner bearing cavity form an air film gap of the air bearing, and the inner air bearing is provided with an air supply channel communicated with the shaft inner bearing cavity. When the rotor system disclosed by the invention is applied to a gas turbine, the cooling of the turbine can be enhanced, and further the temperature in front of the turbine can be further increased, so that the efficiency of the gas turbine is improved. The invention also discloses a gas turbine.

Description

Rotor system and gas turbine

Technical Field

The invention belongs to the field of heat engines, and particularly relates to a rotor system and a 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.

It has been shown that the thermal efficiency and power output of a gas turbine increase with increasing turbine inlet temperature, typically 10% for every 40 ℃ increase in turbine inlet temperature and 1.5% for thermal efficiency [1]. However, the increase of the turbine inlet temperature is limited by the temperature tolerance of the turbine blade material directly exposed to the high-temperature combustion gas and the cooling effect of the turbine blade, and the great increase of the turbine inlet temperature may cause the structural strength of the turbine blade to be reduced, thereby causing the deformation or ablation failure of the blade. Therefore, the turbine blade directly determines the performance level of the gas turbine to a certain extent, and the key technical problem of developing a high-performance gas turbine is how to improve the turbine inlet temperature on the premise of meeting the requirement of long-service-life safe operation of the gas turbine.

Li laughing hall, hou ling clouds, yanmin, et al modern gas turbine technology [ M ]. Beijing: aeronautical industry press, 2006.

Disclosure of Invention

The invention aims to provide a rotor system and a gas turbine, aiming at the defects in the prior art, and the rotor system and the gas turbine can enhance the cooling effect of a turbine, further improve the inlet temperature of the turbine and improve the efficiency of the gas turbine.

The invention adopts the following technical scheme:

in a first aspect, an embodiment of the present invention provides a rotor system, including a rotating shaft, a compressor and a turbine which are axially and sequentially mounted on the rotating shaft, and an inner air bearing located at one axial end of the rotating shaft, where the turbine has a hollow structure and includes a turbine inner cavity and a turbine film hole which are connected; a shaft connecting through hole is formed in the position, corresponding to the turbine, of the rotating shaft, and an in-shaft bearing cavity is formed in at least one axial end of the rotating shaft; the part of the inner air bearing extending into the shaft inner bearing cavity and the circumferential inner wall of the shaft inner bearing cavity form an air film gap of the air bearing, and the inner air bearing is provided with an air supply channel communicated with the shaft inner bearing cavity.

Furthermore, the inner air bearing is provided with a plurality of first air holes which extend radially and are distributed in the circumferential direction, air inlets of the first air holes are connected with an air source, and air outlets of the first air holes face the circumferential inner wall of the bearing cavity in the shaft.

Further, each first air hole is located between the outer opening of the bearing cavity in the shaft and the air outlet of the air supply channel in the axial direction.

Furthermore, the gas supply channel is provided with a flaring with an increased diameter corresponding to the gas outlet, and the first gas hole is arranged corresponding to the flaring.

Further, the portion of the inner air bearing extending into the shaft inner bearing cavity includes a circumferentially disposed inner bearing ring, with a portion of the first air hole being disposed in the inner bearing ring.

Furthermore, one end of the rotating shaft corresponding to the inner air bearing is provided with a nose cone, and the inner air bearing is provided with a nose cone air supply hole.

Further, a second thrust bearing is arranged on one side, far away from the inner air bearing, of the nose cone in the axial direction.

Further, the gas pressure provided through the gas supply channel is greater than the turbine front pressure of the turbine.

Further, the air inlet of the air supply channel is connected with the air exhaust end of the air compressor.

Further, at least some of the blades in the turbine include a plurality of turbine film holes located at a leading edge, a trailing edge, and/or a tip of the blade of the turbine.

Further, the turbine film holes at the leading edge of the blade are arranged in an array.

Further, the turbine film holes at the blade tip are reused as bearing jet holes at the turbine.

In a second aspect, an embodiment of the present invention provides a gas turbine, including the rotor system as described above, and a combustion chamber, an inlet end of the combustion chamber is communicated with an exhaust end of the compressor, an outlet end of the combustion chamber is provided with a guide vane assembly, and the guide vane assembly is located in front of the turbine.

Further, the turbine still includes turbine thrust jet hole, and turbine thrust jet hole's gas outlet is towards the first support wall surface of stator assembly.

Further, the gas turbine engine also includes a second bearing housing, the inner air bearing mounted to the second bearing housing by a damping assembly.

According to the rotor system provided by the embodiment of the invention, when the rotor system is applied to a gas turbine, the turbine with a hollow structure is arranged, and a cooling air film is formed on the outer wall surface of the turbine in the operation process of the gas turbine to protect the turbine, so that the gas temperature before the turbine can be further increased, and the efficiency of the gas turbine can be improved. And, through set up axle inner bearing chamber and axle through-hole in the pivot to and set up the interior air bearing that has air feed channel, can support when realizing the pivot, for the turbine provides pressure gas, and the tip atmoseal of axle inner bearing chamber is realized to the air film through air bearing, thereby guarantees the air feed stability of turbine, so that the outer wall of turbine forms stable cooling air film, guarantees the cooling effect.

Drawings

Other features, objects and advantages of the invention 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 schematic structural view of a rotor system according to an embodiment of the present invention;

FIG. 2 is an enlarged, fragmentary schematic view of the turbine of FIG. 1;

FIG. 3 is an enlarged view of the spindle of FIG. 1;

FIG. 4 is a schematic structural view of one embodiment of the inner air bearing of FIG. 1;

FIG. 5 is a schematic structural view of another embodiment of the inner air bearing of FIG. 1;

FIG. 6 is a schematic structural view of another embodiment of the inner air bearing of FIG. 1;

FIG. 7 is a schematic structural view of a rotor system according to another embodiment of the present invention;

FIG. 8 is a schematic structural view of a rotor system according to yet another embodiment of the present invention;

FIG. 9 is a schematic structural view of a rotor system according to yet another embodiment of the present invention;

FIG. 10 is a schematic structural diagram of an embodiment of a turbine in a rotor system according to an embodiment of the present invention;

FIG. 11 is a schematic structural diagram of another embodiment of a turbine in a rotor system according to an embodiment of the present invention;

FIG. 12 is a sectional view taken along line B-B of FIG. 11;

FIG. 13 is a first angular schematic of a flow field of a turbine according to an embodiment of the present invention;

FIG. 14 is a second angular schematic view of a flow field of a turbine according to an embodiment of the present invention;

FIG. 15 is a schematic illustration of a temperature field of a turbine according to an embodiment of the invention;

FIG. 16 is a schematic block diagram of a gas turbine according to an embodiment of the present invention;

FIG. 17 is an enlarged view of a portion of the turbine of FIG. 16;

FIG. 18 is an enlarged partial schematic view of an embodiment of the inner air bearing of FIG. 16;

FIG. 19 is an enlarged partial schematic view of another embodiment at the inner air bearing of FIG. 16.

Detailed Description

Features and exemplary embodiments of various aspects of the present invention will be described in detail below, and in order to make objects, technical solutions and advantages of the present invention more apparent, the present invention 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 invention and are not to be construed as limiting the invention. It will be apparent to one skilled in the art that the present invention 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 invention by illustrating examples of the present invention.

The efficiency of a gas turbine is positively correlated to the pre-turbine temperature. However, when the temperature in front of the turbine is too high and exceeds the heat resistance limit of the turbine material, the turbine cannot normally and continuously operate, and therefore, efforts are made to develop materials having higher heat resistance temperatures, but the development progress is slow and the price of new materials is high, resulting in a great increase in the cost of the gas turbine.

The inventors have discovered that the turbine may be protected by film or liquid cooling to improve the turbine's material stability at higher pre-turbine temperatures. However, the centrifugal force of the rotation of the turbine alone is used to increase the cooling air pressure, which is often lower or slightly greater than the static pressure in front of the turbine, and thus an effective cooling air film is not formed. The liquid film cooling has high requirements on cooling liquid, such as deionized water, and the cooling liquid needs to be continuously consumed, so that the cooling liquid is difficult to recycle, and the cost is increased.

Therefore, there is a need for a rotor system which, when applied to a gas turbine, can improve the cooling effect of the turbine, and thus can achieve an increase in efficiency by increasing the temperature before the turbine, and which ensures that cooling is continuous and easy to achieve, and that controls manufacturing and modification costs.

To achieve the above object, as shown in fig. 1, fig. 1 is a schematic structural diagram of a rotor system according to an embodiment of the present invention. The invention provides a rotor system which comprises a rotating shaft 100, a compressor 200 and a turbine 300 which are sequentially arranged on the rotating shaft 100 in the axial direction, and an inner air bearing 510 positioned at one end of the rotating shaft 100 in the axial direction.

The compressor 200 may be an axial compressor, a centrifugal compressor, or a diagonal compressor. In some embodiments, the compressor 200 may include a compressor wheel and diffuser. The intake end of the compressor 200 communicates with the external environment for air induction, and the intake air (e.g., air) is compressed by the compressor 200 and then enters the combustion chamber through the exhaust end of the compressor 200.

The turbine 300 may be an axial turbine. In other embodiments, the turbine 300 may also be a centrifugal turbine. The material of the turbine 300 may be a high temperature resistant material, such as nickel or a nickel alloy. The turbine 300 is generally coupled to an exhaust end of the combustor 400 to receive the high temperature combustion gases from the combustor 400 and to utilize the high temperature combustion gases to produce work.

Specifically, as shown in fig. 2, fig. 2 is a partially enlarged schematic view of the turbine of fig. 1, and the turbine 300 has a hollow structure and includes a turbine inner cavity 320 and a turbine film hole 302 connected thereto. Fig. 1 and 2 exemplarily show that the turbine 300 is a hollow turbine, and specifically includes a turbine housing 310, a turbine inner cavity 320 is formed by the turbine housing 310, and a turbine film hole 302 is opened in the turbine housing 310 and communicates with the turbine inner cavity 320. The hollow turbine 300 may be formed from two or more pieces of housing that are fixedly attached (e.g., welded). In other embodiments, the turbine inner cavity 320 may also be a communication channel to supply gas to the turbine film holes 302. In other embodiments, baffles or labyrinth structures may be disposed within the turbine interior cavity 320 to increase the cooling effect within the turbine to further enhance the overall cooling effect of the turbine 300.

The material of the shaft 100 may be steel, or other suitable metals, alloys, or composites. The shaft 100 is supported by bearings to the casing or bearing housing of the gas turbine. The bearing is preferably an air bearing, and may be another non-contact bearing such as a magnetic bearing or a gas-magnetic hybrid bearing.

Specifically, as shown in fig. 3, fig. 3 is an enlarged schematic view of the rotating shaft of fig. 1, and the rotating shaft 100 has a shaft connecting through hole 150 at a position corresponding to the turbine 300, so as to provide cooling air for the turbine 300 through the shaft connecting through hole 150 through the inside of the rotating shaft 100. Also, at least one axial end of the rotating shaft 100 has an inner shaft bearing cavity 120, fig. 3 shows that the inner shaft bearing cavity 120 is located at one end corresponding to the compressor 200, and in other embodiments, the inner shaft bearing cavity 120 may also be located at the other end opposite to the compressor 200. The shaft inner bearing chamber 120 communicates with the shaft connecting through hole 150 through the shaft inner air passage 140, and the shaft connecting through hole 150 communicates with the turbine inner chamber 320 through the turbine communicating hole 301 of the turbine 300. Thus, the cooling air from the outside enters the shaft inner bearing cavity 120, then enters the turbine inner cavity 320 through the shaft inner air passage 140 and the shaft connecting through hole 150, and then is ejected through the turbine air film hole 302 to form a cooling air film on the outer wall surface of the turbine 300.

The inner air bearing 510 is a stator component with respect to the shaft 100, and the inner air bearing 510 may be mounted in a housing or a bearing housing of a gas turbine, for example. The inner air bearing 510 extends at least partially into the shaft inner bearing cavity 120, and a gas film gap of the gas bearing is formed between the part of the inner air bearing 510 extending into the shaft inner bearing cavity 120 and the circumferential inner wall of the shaft inner bearing cavity 120. The inner air bearing 510 supports the rotation of the rotation shaft 100, and the inner air bearing 510 is located at one end of the rotation shaft 100 to at least partially close the opening of the shaft inner bearing cavity 120, and the remaining gap is air-sealed by an air film formed during the operation of the inner air bearing 510. The inner air bearing 510 has an air supply passage 511 in communication with the shaft inner bearing cavity 120 to provide turbine cooling air to the shaft inner bearing cavity 120.

According to the rotor system of the embodiment of the invention, when the rotor system is applied to a gas turbine, by arranging the turbine 300 with a hollow structure, when the rotor system is applied to the gas turbine, a cooling air film is formed on the outer wall surface of the turbine 300 during the operation of the gas turbine, so that the turbine 300 is protected, and the gas temperature before the turbine can be further increased, so that the efficiency of the gas turbine can be improved. In addition, by arranging the shaft inner bearing cavity 120 and the shaft connecting through hole 301 in the rotating shaft 100 and arranging the inner air bearing 510 with the air supply channel 511, pressure air can be supplied to the turbine 300 while the rotating shaft 100 is supported, and air sealing of the end part of the shaft inner bearing cavity 120 is realized through an air film of the inner air bearing 510, so that the air supply stability of the turbine 300 is ensured, a stable cooling air film is formed on the outer wall surface of the turbine 300, and the cooling effect is ensured.

Further, the pressure of the gas supplied through the gas supply passage 511 is greater than the turbine front pressure of the turbine 300, which ensures that the cooling gas can be ejected through the turbine film hole 302 against the turbine front pressure to form a cooling film.

Specifically, an air inlet of the air supply passage 511 is connected to an exhaust end of the compressor 200, and the pressure at the exhaust end of the compressor 200 is higher than the turbine front pressure of the turbine 300.

Further, as shown in fig. 4, fig. 4 is a schematic structural diagram of an embodiment of the inner air bearing in fig. 1, the inner air bearing 510 has a plurality of first air holes 512 extending radially and arranged circumferentially, air inlets of the first air holes 512 are connected to an air source, and air outlets of the first air holes 512 face a circumferential inner wall of the inner shaft bearing cavity 120. The gas source may be an external gas source, such as an air pump. The air supply may also be the compressor 200, for example, the inlet of the first air hole 512 is communicated with the exhaust end of the compressor 200. In fig. 4, the inlet of the first air hole 512 is shown to be connected to the air supply passage 511, and the air supply passage 511 is connected to the air source, and in alternative embodiments, the inlet of the first air hole 512 may be connected to the air source through other passages.

Specifically, each first air hole 512 is located between the outer opening of the shaft inner bearing cavity 120 and the air outlet of the air supply passage 511 in the axial direction, so that the air outlet of the air supply passage 511 is located inside the shaft inner bearing cavity 120 and air sealing can be achieved through each first air hole 512.

During operation of the gas turbine to which the rotor system is applied, the first air holes 512 inject air toward the circumferential wall surface of the shaft inner bearing cavity 120 to form an air film that supports the rotation of the rotating shaft 100 and forms an air seal between the rotating shaft 100 and the inner air bearing 510, so that turbine cooling air supplied from the air supply passage 511 of the inner air bearing 510 to the shaft inner bearing cavity 120 does not leak as much as possible to ensure a cooling effect.

In some alternative embodiments, the first air hole 512 is a stepped hole with a large end of the hole facing the inner air bearing 510, which may further increase the incoming air flow velocity to further enhance the air film strength.

In some alternative embodiments, the first air holes 512 are arranged in more than two circles along the axial direction to increase the air output, ensure the strength of the air film, and increase the stability of the inner air bearing 510.

In some alternative embodiments, as shown in fig. 5, fig. 5 is a schematic structural view of another embodiment of the internal air bearing in fig. 1, the air supply passage 511 has a flared opening 513 with an increased diameter corresponding to the air outlet, and the first air hole 512 is opened corresponding to the flared opening 513. The provision of a flared mouth 513 of a larger diameter than the original gas supply passage 511 facilitates a machining tool (e.g., a hook cutter) to machine the large-diameter end of the first gas orifice 512 deep into the flared mouth 513, which may then be used to machine the small-diameter end of the first gas orifice 512, for example, by laser drilling.

In other alternative embodiments, as shown in fig. 6, fig. 6 is a schematic diagram of a further embodiment of the inner air bearing of fig. 1, wherein the portion of the inner air bearing 510 extending into the shaft inner bearing cavity 120 includes a circumferentially disposed inner bearing ring 512. The inner bearing ring 512 is in the shape of a collar, and can be sleeved on the body of the inner air bearing 510 with an interference fit. A part of the first air hole 512 is disposed in the inner bearing ring 512, that is, a part of the first air hole 512 is opened along the circumferential direction of the inner bearing ring 512, and another part of the first air hole 512 is disposed on the body of the inner air bearing 510, and the two parts are connected to each other and together form the first air hole 512. As shown in fig. 6, when the first air hole 512 is a stepped hole, the small end of the first air hole 512 is disposed on the inner bearing ring 512. The arrangement of this embodiment can be convenient for process first gas pocket 512, especially process the first gas pocket 512 for the shoulder hole, and the processing mode can be for example for adopt the broach to process the aperture main aspects of inner race 512, and the rethread laser processes the aperture minor aspects.

Further, as shown in fig. 7, fig. 7 is a schematic structural diagram of a rotor system according to another embodiment of the present invention, and the rotor system further includes a first radial bearing 520 and a first thrust bearing 530 disposed between the compressor 200 and the turbine 300. The first radial bearing 520 is an external air bearing sleeved on the outer circumferential surface of the rotating shaft 100. The air film medium of the air bearing referred to herein may be a single component gas, ambient air gas, or other mixed component gas. The number of the first radial bearings 520 may be 2 or more, and 2 or more first radial bearings 520 may be provided on both sides of the first thrust bearing 530 in the axial direction. The rotating shaft 100 is provided with a thrust disc 130, and the first thrust bearings 530 are disposed on both axial sides of the thrust disc 130.

In some alternative embodiments, as shown in fig. 8, fig. 8 is a schematic structural diagram of a rotor system according to another embodiment of the present invention, and one end of the rotating shaft 100 corresponding to the inner air bearing 510 is provided with a nose cone 160. The nose cone 160 may be integrally formed with the rotating shaft 100, or may be fixedly mounted on the rotating shaft 100 by welding or connecting means. Nose cone 160 has a thrust surface axially toward the end of inner air bearing 510. Inner air bearing 510 has a nose cone air supply hole 515, and an air inlet end of nose cone air supply hole 515 may communicate with air supply passage 511, and an air outlet of nose cone air supply hole 515 faces a thrust surface of nose cone 160. The pressure gas ejected from the nose cone gas supply hole 515 can give axial thrust to the nose cone 160, which facilitates the force balance in the axial direction of the rotor system. In other embodiments, the air inlet end of the nose cone air supply hole 515 may be connected to the air supply via other channels.

Further, as shown in fig. 9, fig. 9 is a schematic structural diagram of a rotor system according to still another embodiment of the present invention, and a second thrust bearing 540 is disposed on a side of the nose cone 160 axially far from the inner air bearing 510. The second thrust bearing 540 may be disposed to be vertical or inclined according to the surface form of the nose cone 160. The second thrust bearing 540 can further facilitate force balancing in the axial direction of the rotor system. In this embodiment, when the nose cone 160 and the second thrust bearing 540 can satisfy the axial thrust requirement, the thrust disc 130 and the first thrust bearing 530 may be eliminated, so as to shorten the length of the rotating shaft 100, reduce the weight of the rotating shaft 100, and facilitate improving the rotating performance of the rotor system.

Further, as shown in fig. 10, fig. 10 is a schematic structural diagram of an embodiment of a turbine in a rotor system according to an embodiment of the present invention, and at least a part of blades in the turbine 300 include a plurality of turbine film holes 302. The turbine film holes 302 are located at the leading edge and tip of the blades of the turbine 300. A plurality of turbine film holes 302 at the leading edge of the blade may be arranged radially of the turbine 300. The turbine film holes 302 are located at different locations to meet the cooling requirements at each location and to provide fine control over the formation of the cooling film.

Specifically, as shown in fig. 11 and 12, fig. 11 is a schematic structural view of another embodiment of a turbine in a rotor system according to an embodiment of the present invention, and fig. 12 is a sectional view taken along B-B of fig. 11, and the turbine film holes 302 located at the leading edge of the blade are arranged in an array to meet cooling requirements in different areas and directions and to facilitate air flow diversion.

Further, as shown in FIG. 11, the turbine film holes 302 at the tip of the blade may be multiplexed as bearing jet holes at the turbine. On the one hand, the turbine film holes 302 located at the blade tip are used for cooling the blade tip, on the other hand, radial gas thrust can be formed between the blade tip with the turbine film holes 302 and the outer shell, and pressure gas ejected from the turbine film holes 302 of the blade tip can radially support the turbine 300 to a certain extent, so that the improvement of the rotational stability of a rotor system is facilitated.

Further, as shown in fig. 11, the turbine film holes 302 may also be located at the trailing edge of the blade of the turbine 300, and the air flow guiding is facilitated by the air outlet from the trailing edge.

Further referring to fig. 13 and 14, fig. 13 is a first angle schematic view of a flow field of a turbine according to an embodiment of the present invention, and fig. 14 is a second angle schematic view of a flow field of a turbine according to an embodiment of the present invention, wherein a schematic view of an air jet flow field with a turbine front pressure is shown with air jet holes 302, the air jet being capable of forming a cooling air film on the blade surface of the turbine 300, and the cooling air being directed against the blade surface towards the blade trailing edge.

As further shown in fig. 15, fig. 15 is a schematic view of a temperature field of a turbine according to an embodiment of the present invention, and a scale on the left side is a temperature scale, and the lighter the color is, the higher the temperature is, as can be seen from the figure, the rotor system according to an embodiment of the present invention can effectively reduce the temperature of the blades of the turbine 300, so as to ensure material performance at a higher turbine inlet temperature, improve efficiency, and meet the premise of long-life safe operation of a gas turbine.

Referring to fig. 16, fig. 16 is a schematic structural diagram of a gas turbine according to an embodiment of the present invention, and the present invention further provides a gas turbine including a rotor system according to any of the embodiments, and a combustor 400. The combustor 400 may be an annular combustor, a mono-can combustor, a can-annular combustor, or the like. The combustion chamber 400 may be disposed around the rotating shaft 100, and an inlet end of the combustion chamber 400 communicates with an exhaust end of the compressor 200, and an outlet end of the combustion chamber 400 is provided with a guide vane assembly 700, and the guide vane assembly 700 is located in front of the turbine 300.

According to the gas turbine of the embodiment of the invention, the turbine 300 with the hollow structure is arranged, the cooling air film is formed on the outer wall surface of the turbine 300 during the operation of the gas turbine, the turbine 300 is protected, and the gas temperature before the turbine can be further improved, so that the efficiency of the gas turbine is improved. In addition, by arranging the shaft inner bearing cavity 120 and the shaft connecting through hole 301 in the rotating shaft 100 and arranging the inner air bearing 510 with the air supply channel 511, pressure air can be supplied to the turbine 300 while the rotating shaft 100 is supported, and the end air seal of the shaft inner bearing cavity 120 is realized through the air film of the inner air bearing 510, so that the air supply stability of the turbine 300 is ensured, a stable cooling air film is formed on the outer wall surface of the turbine 300, and the cooling effect is ensured.

Further, the gas turbine further includes a first bearing housing 600, and a first radial bearing 520 and a first thrust bearing 530 may be installed in the first bearing housing 600.

Further, as shown in fig. 17, fig. 17 is a partial enlarged view of the turbine in fig. 16, and the gas turbine further includes a guide vane assembly 700, wherein the guide vane assembly 700 includes a first support 710, a second support 730, and a blade assembly 720 having an axial air passage between the two supports. The turbine 300 further comprises a turbine thrust jet hole 305, an air outlet of the turbine thrust jet hole 305 faces the wall surface of the first support 710 of the guide vane assembly 700, and pressure air ejected from the turbine thrust jet hole 305 can form axial thrust to facilitate axial balance of a rotor system of the gas turbine. Further, both sides of the turbine thrust nozzle 305 may be provided with air sealing holes 306, the diameter of the air sealing holes 306 is smaller than that of the turbine thrust nozzle 305, and the pressure air ejected from the air sealing holes 306 can form an air curtain seal to seal the air ejected from the turbine thrust nozzle 305 as much as possible to improve the thrust.

Further, as shown in fig. 18 and 19, fig. 18 is a partial enlarged view of an embodiment of the inner air bearing in fig. 16, fig. 19 is a partial enlarged view of another embodiment of the inner air bearing in fig. 16, the gas turbine further includes a second bearing seat 800, the inner air bearing 510 is mounted on the second bearing seat 800 through a damping assembly 830, wherein the damping assembly 830 may be an elastic member (e.g., a sealing ring) multiplexed as a sealing member, and the damping assembly 830 can provide an air seal while compensating for the anisotropic runout of the inner air bearing 510. Fig. 18 and 19 each show a different arrangement of the second bearing housing 800. The second bearing housing 800 is provided with a passage 810 for supplying air to the air supply passage 511.

In the description of the present invention, 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 invention 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 invention. 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 invention, "a plurality" means two or more unless otherwise specified.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly and may be, for example, fixedly connected, detachably connected, or integrally connected; 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 meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

In the description of the present invention, reference to the description of the terms "one embodiment," "some embodiments," "an illustrative embodiment," "an example," "a specific example," or "some examples" or the like 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 invention. 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 above-described embodiments of the present invention, these embodiments are not intended to be exhaustive or to limit the invention to the precise embodiments disclosed. 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 invention and the practical application, to thereby enable others skilled in the art to best utilize the invention and various embodiments with various modifications as are suited to the particular use contemplated. The invention is limited only by the claims and their full scope and equivalents.

Claims

1. A rotor system is characterized by comprising a rotating shaft, a gas compressor, a turbine and an inner air bearing, wherein the gas compressor and the turbine are sequentially arranged on the rotating shaft in the axial direction, the inner air bearing is positioned at one axial end of the rotating shaft,

the turbine is of a hollow structure and comprises a turbine inner cavity and a turbine film hole which are connected;

a shaft connecting through hole is formed in the position, corresponding to the turbine, of the rotating shaft, and an inner shaft bearing cavity is formed in at least one axial end of the rotating shaft, the inner shaft bearing cavity is communicated with the shaft connecting through hole through an inner shaft air passage, and the shaft connecting through hole is communicated with the inner chamber of the turbine through a turbine communicating hole of the turbine;

the inner air bearing extends to the part in the shaft inner bearing cavity and forms an air film gap of the air bearing between the circumferential inner wall of the shaft inner bearing cavity, and the inner air bearing is provided with an air supply channel communicated with the shaft inner bearing cavity.

2. The rotor system of claim 1, wherein the inner air bearing has a plurality of first air holes extending radially and arranged circumferentially, air inlets of the first air holes are connected with an air source, and air outlets of the first air holes face to the circumferential inner wall of the bearing cavity in the shaft; and the axial position of each first air hole is positioned between the external opening of the bearing cavity in the shaft and the air outlet of the air supply channel.

3. The rotor system according to claim 2, wherein the gas supply channel has a flared opening with an increased diameter corresponding to the gas outlet thereof, and the first gas hole is opened corresponding to the flared opening;

or, the part of the inner air bearing extending into the shaft inner bearing cavity comprises an inner bearing ring arranged along the circumferential direction, and a part of the first air hole is arranged in the inner bearing ring.

4. The rotor system as in claim 2, wherein an end of said shaft corresponding to said inner air bearing has a nose cone, said inner air bearing having a nose cone air supply hole.

5. The rotor system of claim 4, wherein a side of the nose cone axially distal from the inner air bearing is provided with a second thrust bearing.

6. A rotor system according to claim 1, wherein the gas pressure provided by the gas supply channel is greater than the turbine front pressure of the turbine, and/or wherein the gas inlet of the gas supply channel is connected to the gas outlet of the compressor.

7. The rotor system of claim 1, wherein at least some of the blades in the turbine comprise a plurality of said turbine film holes located at a leading edge, a trailing edge and/or a tip of the turbine blade;

the turbine air film holes positioned at the front edge of the blade are arranged in an array;

and the turbine air film hole positioned at the blade top is reused as a bearing spray hole at the turbine.

8. A gas turbine comprising a rotor system according to any one of claims 1 to 7, and a combustion chamber, an inlet end of the combustion chamber communicating with an exhaust end of the compressor, an outlet end of the combustion chamber being provided with a guide vane assembly, the guide vane assembly being located in front of the turbine.

9. The gas turbine of claim 8, wherein the turbine further comprises a turbine thrust jet hole having an outlet facing the wall surface of the first seat of the vane assembly.

10. The gas turbine of claim 8, further comprising a second bearing housing, said inner air bearing being mounted to said second bearing housing by a damping assembly.