CN218062463U - Rotor system and gas turbine - Google Patents

Abstract

The utility model discloses a rotor system, including pivot, turbine and housing part, turbine fixed mounting is in the pivot, and the housing part centers on the turbine setting, and the turbine has hollow structure and including the turbine inner chamber and the turbine gas film hole that are connected, the blade top that the housing part corresponds the turbine has annular first bearing surface, and turbine gas film hole is located the blade top of turbine and gas outlet orientation first bearing surface. The utility model discloses a rotor system sets up gas bearing structure through the turbine end at rotor system, supports the turbine end to turbine end rotational stability has effectively been improved. The utility model also discloses a gas turbine.

Description

Rotor system and gas turbine

Technical Field

The utility model belongs to the heat engine field, concretely relates to rotor system and 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 for converting heat energy generated by fuel combustion into mechanical work and outputting 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.

In the rotor system of the gas turbine, the turbine needs to rotate at high speed and the working temperature is high, for example, for a low-power gas turbine, the rotating speed of the rotor system of the gas turbine can reach or exceed 140000RPM (revolutions per minute), the working temperature of the turbine can reach 950-1000 ℃, the working linear speed of the turbine wheel is extremely high, and thus the bearing centrifugal force is up to 100MPa. The high temperature makes it difficult to provide bearings at the turbine to provide rotational support, making the turbine susceptible to large amplitude oscillations.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a rotor system to the not enough of prior art existence, and gas turbine. The utility model discloses a turbine end at rotor system gas turbine sets up the gas bearing structure, supports the turbine end to turbine end stability in rotation has effectively been improved.

The utility model adopts the following technical scheme:

in a first aspect, an embodiment of the present invention provides a rotor system, including pivot, turbine and housing part, turbine fixed mounting is in the pivot, and the housing part centers on the turbine setting, and the turbine has hollow structure and including the turbine inner chamber and the turbine film hole that are connected, and the blade top that the housing part corresponds the turbine has annular first bearing surface, and turbine film hole is located the blade top of turbine and gas outlet orientation first bearing surface.

Furthermore, the number of the turbine film holes of at least part of the blades in the turbine is multiple, and the multiple turbine film holes positioned at the blade top are arranged in an array.

Further, part of the turbine film holes are positioned at the blade leading edge and/or the blade trailing edge of the turbine.

Further, the turbine film hole is a stepped hole, and the radial small end faces the first bearing surface.

Further, the turbine still includes the turbine inlet port, and the turbine inlet port sets up and communicates with the turbine inner chamber near the pivot.

Further, the turbine intake aperture is in communication with the outside atmosphere.

Furthermore, the rotating shaft is provided with an air supply channel, one end of the air supply channel is communicated with the turbine air inlet hole, and the other end of the air supply channel is connected to other positions on the rotating shaft.

Further, the rotor system further comprises an inner air bearing, and the other end of the air supply channel is communicated with the inner air bearing.

Further, the rotor system also comprises a first radial bearing and/or a thrust bearing which are arranged in the bearing seat, and the other end of the air supply channel is communicated with an air passage in the bearing seat.

Furthermore, the rotor system also comprises a compressor fixedly arranged on the rotating shaft, and air inlet at the air inlet end of the turbine air inlet hole comes from the air outlet end of the compressor.

Further, the shell component is a guide vane assembly, the guide vane assembly comprises a first support, a second support and a blade group which is located between the two supports and provided with an axial air passage, the turbine further comprises a turbine thrust jet hole, and an air outlet of the turbine thrust jet hole faces to the wall surface of the first support.

In a second aspect, embodiments of the present invention provide a gas turbine, comprising a rotor system as described above, and a combustion chamber, an outlet end of the combustion chamber communicating with an inlet end of the turbine.

According to the utility model discloses rotor system has hollow structure's turbine through the setting to the turbine is including the turbine inner chamber and the turbine gas film hole that are connected, and the gas outlet in turbine gas film hole is towards the first bearing surface of housing part, and pressure gas in the turbine inner chamber spouts to first bearing surface via turbine gas film hole, forms radial holding power, thereby improves the radial swing of turbine when high-speed operation, stability when increasing the turbine and rotating.

Drawings

Other features, objects and advantages of the present invention will become more apparent upon reading of the following detailed description of non-limiting embodiments thereof, with reference to the accompanying drawings, in which like or similar reference characters indicate like or similar features, and which are not drawn to scale.

Fig. 1 is a schematic structural diagram of a rotor system according to an embodiment of the present invention.

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

FIG. 3 is an enlarged, fragmentary schematic view of another embodiment of the turbine of FIG. 1;

FIG. 4 is an enlarged, fragmentary schematic view of yet another embodiment of the turbine of FIG. 1;

FIG. 5 is an enlarged, fragmentary schematic view of a further embodiment of the turbine of FIG. 1;

fig. 6 is a schematic structural view of a rotor system according to another embodiment of the present invention;

fig. 7 is a schematic structural view of a rotor system according to yet 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 an enlarged, fragmentary schematic view of an embodiment of the turbine of FIG. 8;

fig. 10 is a schematic structural view of a gas turbine according to an embodiment of the present invention.

Detailed Description

The features and exemplary embodiments of various aspects of the present invention will be described in detail below, and in order to make the 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 intended to limit 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 invention by illustrating examples of the invention.

As shown in fig. 1, fig. 1 is a schematic structural diagram of a rotor system according to an embodiment of the present invention, which provides a rotor system, including a rotating shaft 100, a turbine 300 and a housing member 700, wherein the turbine 300 is fixedly mounted on the rotating shaft 100, and the housing member 700 is disposed around the turbine 300.

The material of the rotating shaft 100 may be steel, or may be other suitable metals, alloys, or composite materials. 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.

The housing member 700 may be a portion of the housing or may be other functional components attached to the housing, such as a bracket, bearing block, end block, etc. The housing part 700 has an annular first bearing surface 701 corresponding to the blade tip of the turbine 300. The axial width of the first bearing surface 701 is greater than the axial width of the tip of the turbine 300 to provide a more ample bearing surface and to direct the airflow.

The turbine 300 may be an axial flow 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. When the rotor system is used in a gas turbine, the turbine 300 is typically coupled to the 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 an enlarged partial schematic view of an embodiment of the turbine of FIG. 1, the turbine 300 having a hollow structure and including 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 surrounded 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 by fixedly attaching (e.g., welding) two or more pieces of the housing. In other embodiments, the turbine inner cavity 320 may also be a communication channel to supply gas to the turbine film holes 302.

The turbine film hole 302 is located at the tip of the turbine 300 and the outlet port faces the first bearing surface 701. The turbine 300 further includes a turbine inlet hole 301, and the turbine inlet hole 301 is disposed near the rotating shaft 100 and communicates with the turbine inner cavity 320. After being pressurized by centrifugal action when the turbine 300 rotates, the gas entering the turbine inner cavity 320 from the turbine inlet hole 301 is sprayed to the first bearing surface 701 by the turbine film hole 302 at the top of the blade of the turbine 300 to provide radial support force and facilitate the formation of a support film between the first bearing surface 701 and the top of the blade of the turbine 300, thereby forming a gas bearing at the turbine 300.

According to the utility model discloses rotor system, through setting up the turbine 300 that has hollow structure to turbine 300 is including the turbine inner chamber 320 and the turbine gas film hole 301 that are connected, and the gas outlet of turbine gas film hole 301 is towards the first bearing surface 701 of casing part 700, and the pressure gas in the turbine inner chamber 320 spouts to first bearing surface 701 via turbine gas film hole 302, forms radial holding power, thereby improves the radial swing of turbine 300 when high-speed running, stability when increasing turbine 300 and rotating.

Further, as shown in FIG. 3, FIG. 3 is a partial enlarged schematic view of another embodiment of the turbine of FIG. 1, and the number of the turbine film holes 302 of at least some of the blades in the turbine 300 may be plural. In some embodiments, the number of turbine film holes 302 is the same for each blade of the turbine, which provides more uniform radial support. In other embodiments, the number of the turbine film holes 302 of each blade of the turbine is alternatively the same, so that the pressure of the gas ejected from the turbine film holes 302 can be ensured under the condition of limited gas supply amount, and a supporting effect is realized.

Further, as shown in fig. 3, in a single blade of the turbine 300, the plurality of turbine film holes 302 at the tip of the blade are arranged in an array, such as one-row and multiple-column, one-row and multiple-row. The turbine film holes 302 for array air outlet can make air outlet more uniform, and facilitates detail adjustment (aperture, relative position relation and the like of each turbine film hole 302) to match design parameters of a rotor system.

Further, as shown in FIG. 3, the turbine diaphragm bore 302 is a stepped bore with a radially small end facing the first bearing surface 701. The stepped hole may further increase the airflow velocity to further enhance the supporting force.

Further, as shown in fig. 4, fig. 4 is a partial enlarged schematic view of a further embodiment of the turbine in fig. 1, in a single blade of the turbine 300, a part of the turbine film holes 302 may be located at a leading edge of the blade of the turbine, and the pressure gas ejected from the turbine film holes 302 located at the leading edge of the blade can form a cooling film on the surface of the blade, and when the rotor system is applied to a gas turbine, the cooling film can protect the turbine, so that the gas temperature before the turbine can be further increased to improve the efficiency of the gas turbine.

Further, as shown in FIG. 5, FIG. 5 is a partial enlarged view of a further embodiment of the turbine of FIG. 1. In a single blade of the turbine 300, a portion of the turbine film holes 302 may be located at the trailing edge of the blade of the turbine, where flow diversion is facilitated by the exit from the trailing edge.

Further, as shown in fig. 6, fig. 6 is a schematic structural diagram of a rotor system according to another embodiment of the present invention, the rotor system further includes a compressor 200 fixedly installed on the rotating shaft 100, and an inlet end of the turbine inlet hole 301 is an outlet end of the compressor 200.

Referring to fig. 2 to 5, the turbine 300 further includes a turbine inlet 301.

In some alternative embodiments, as shown in fig. 6, the turbine air inlet hole 301 may communicate with the external atmosphere, and the air of the external atmosphere is sucked into the turbine inner cavity 320 from the turbine air inlet hole 301 located near the inner diameter of the turbine 300, and is pressurized by the centrifugal effect during the high-speed rotation of the turbine 300, and is ejected to the first bearing surface 701 from the turbine film hole 302 located at the top of the blade of the turbine 300 to provide a radial supporting force, which acts as a gas bearing.

In other alternative embodiments, as shown in fig. 7 and 8, fig. 7 is a schematic structural diagram of a rotor system according to still another embodiment of the present invention, fig. 8 is a schematic structural diagram of a rotor system according to still another embodiment of the present invention, the rotating shaft 100 has a gas supply channel, one end of the gas supply channel is communicated with the turbine gas inlet hole 301, and the other end of the gas supply channel is connected to other positions on the rotating shaft 100, which may be the end surface of the rotating shaft 100 or other axial surface positions of the rotating shaft 100. Other on-axis locations more suitable for supplying pressure can be utilized through the supply air channel to provide more stable and higher pressure air for the turbine 300.

Specifically, in one embodiment, as shown in fig. 7, the rotor system further includes a first radial bearing 520 and/or a thrust bearing 530 installed in a bearing housing (not shown), and the other end of the air supply channel is communicated with an air path in the bearing housing, which may be communicated with the air outlet end of the compressor 200, or may be communicated with the air supply of the first radial bearing 520 or the thrust bearing 530, and may be communicated with the air outlet end of the first radial bearing 520 or the thrust bearing 530.

In another embodiment, as shown in FIG. 8, the rotor system further includes an inner air bearing 510, and the other end of the air supply channel communicates with the inner air bearing 510. The inner air bearing 510 may be mounted within a housing or housing, for example. The inner air bearing 510 extends at least partially into the end bearing cavity of the air supply passage, and an air film gap of the air bearing is formed between the part of the inner air bearing 510 extending into the end bearing cavity and the circumferential inner wall of the end bearing cavity. 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 end bearing cavity, and the remaining gap is air-sealed by an air film formed during the operation of the inner air bearing 510.

Further, as shown in fig. 8 and 9, fig. 9 is a partially enlarged schematic view of an embodiment of the turbine in fig. 8, the casing member 700 is a guide vane assembly 700, the guide vane assembly 700 includes a first seat 710, a second seat 730, and a blade set 720 having an axial air passage located between the two seats, and the turbine 300 further includes a turbine thrust nozzle hole 305, and an air outlet of the turbine thrust nozzle hole 305 faces a wall surface of the first seat 710. The pressure gas ejected from the turbine thrust nozzle 305 can form axial thrust, and axial balance of the rotor system is facilitated. Further, air sealing holes 306 may be disposed on two sides of the turbine thrust nozzle 305, a diameter of each air sealing hole 306 is smaller than a diameter of the turbine thrust nozzle 305, and pressure air ejected from the air sealing holes 306 can form an air curtain seal to seal air ejected from the turbine thrust nozzle 305 as much as possible to improve thrust.

As shown in fig. 10, fig. 10 is a schematic structural diagram of a gas turbine according to an embodiment of the present invention. The present invention also provides a gas turbine, including the rotor system of any of the foregoing 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 about the shaft 100 with an inlet end of the combustion chamber 400 communicating with an exhaust end of the compressor and an outlet end of the combustion chamber 400 communicating with an intake end of the turbine 300.

According to the utility model discloses gas turbine has hollow structure's turbine 300 through the setting, and turbine 300 is including the turbine inner chamber 320 and the turbine gas film hole 301 that are connected, the gas outlet of turbine gas film hole 301 is towards the first bearing surface 701 of casing part 700, pressure gas in the turbine inner chamber 320 spouts to first bearing surface 701 via turbine gas film hole 302, form radial support power, thereby improve turbine 300's radial swing when high-speed operation, stability when increasing turbine 300 and rotating, be favorable to gas turbine's steady operation.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", and the like, indicate the orientation or positional relationship indicated based on the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present 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 is to 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 meaning 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.

While embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.

Claims (10)

1. A rotor system comprises a rotating shaft, a turbine and a shell component, wherein the turbine is fixedly installed on the rotating shaft, the shell component is arranged around the turbine, the turbine is of a hollow structure and comprises a turbine inner cavity and a turbine film hole which are connected, the shell component is provided with an annular first bearing surface corresponding to a blade top of the turbine, the turbine film hole is located on the blade top of the turbine, and an air outlet faces the first bearing surface.

2. The rotor system of claim 1, wherein the number of the turbine film holes of at least some blades in the turbine is plural, and the plural turbine film holes at the tip of the turbine are arranged in an array; and/or the presence of a gas in the gas,

and part of the turbine film holes are positioned at the blade leading edge and/or the blade trailing edge of the turbine.

3. The rotor system of claim 1, wherein the turbine film hole is a stepped hole with a radially small end facing the first bearing surface.

4. The rotor system as in claim 1, wherein the turbine further comprises a turbine air intake aperture disposed proximate the shaft and in communication with the turbine interior cavity.

5. The rotor system as in claim 4, wherein the turbine air intake vent is in communication with the outside atmosphere; alternatively, the first and second electrodes may be,

the rotating shaft is provided with an air supply channel, one end of the air supply channel is communicated with the turbine air inlet, and the other end of the air supply channel is connected to other positions on the rotating shaft.

6. The rotor system as set forth in claim 5 further including an inner air bearing, the other end of said air supply passage communicating with said inner air bearing.

7. A rotor system according to claim 5, further comprising a first radial bearing and/or thrust bearing mounted in a bearing housing, the other end of the gas supply channel being in communication with a gas path in the bearing housing.

8. The rotor system as in claim 4, further comprising a compressor fixedly mounted on said shaft, wherein the inlet end of said turbine inlet is fed from the outlet end of said compressor.

9. The rotor system of claim 1, wherein the housing component is a vane assembly comprising a first seat, a second seat, and a blade set with an axial air passage between the two seats, the turbine further comprising a turbine thrust jet hole having an outlet facing the first seat wall.

10. A gas turbine comprising a rotor system according to any one of claims 1 to 9, and a combustion chamber, the outlet end of which communicates with the inlet end of the turbine.

Images