CN220101352U - Gas turbine and vehicle - Google Patents

Abstract

The utility model relates to the technical field of power devices, and discloses a gas turbine and a vehicle, wherein the gas turbine comprises: the device comprises a compressor, a casing, a volute, a combustion chamber and a turbine; the volute and the casing are both annular, the volute is positioned in the casing and is coaxially arranged with the casing, the air outlet of the air compressor is communicated with the air inlet of the interlayer space, and the interlayer space represents the space between the casing and the volute, so that the air compressor can conveniently convey compressed high-pressure air into the interlayer space; the gas outlet of the interlayer space is communicated with the gas inlet of the combustion chamber, the gas outlet of the combustion chamber is communicated with the gas inlet of the volute, the burnt high-temperature and high-pressure gas is conveyed into the volute, the gas outlet of the volute is communicated with the gas inlet of the turbine, and the burnt gas is conveyed to the turbine through the volute to perform work; through the elastic connection between the volute and the casing along the axial direction and/or the radial direction, the deformation or movement of the volute can be buffered, the overall equivalent stress of the volute is reduced, and the service life of the volute is prolonged.

Description

Gas turbine and vehicle

Technical Field

The utility model relates to the technical field of power devices, in particular to a gas turbine and a vehicle.

Background

The gas turbine is used as an internal combustion type power machine which takes continuous flowing gas as working medium to drive an impeller to rotate so as to convert chemical energy into work, and the internal combustion type power machine consists of three main core components: a compressor, a combustor, and a gas turbine. The compressor compresses air into high-pressure air, the high-pressure air enters a combustion chamber to be mixed with fuel for combustion to form high-temperature fuel gas, and the high-temperature fuel gas enters a turbine for expansion work to enable the turbine to rotate so as to drive the compressor and a generator to rotate for power generation. The volute is an intermediate transition section for connecting the combustion chamber and the gas turbine, the inlet is a combustion chamber outlet, the temperature is extremely high and can reach over 1100K, the inner edge of the outlet is cooled by cooling gas, the temperature can reach 500K, and the whole volute bears extremely high temperature difference, so that the service life of the volute is directly influenced.

In recent years, in order to improve the performance of the gas turbine, the temperature of the combustion chamber is continuously increased, the temperature difference of the volute is also continuously increased, and the temperature difference is greatly limited by the traditional volute structure.

Disclosure of Invention

The utility model discloses a gas turbine and a vehicle, which are used for relieving the limit of a volute on temperature difference and prolonging the service life of the volute.

In order to achieve the above purpose, the present utility model provides the following technical solutions:

in a first aspect, there is provided a gas turbine comprising: the device comprises a compressor, a casing, a volute, a combustion chamber and a turbine; the volute and the casing are annular, the volute is positioned in the casing and is coaxially arranged with the casing, an air outlet of the air compressor is communicated with an air inlet of an interlayer space, and the interlayer space represents a space between the casing and the volute so that the air compressor can convey compressed high-pressure air into the interlayer space; the gas outlet of the interlayer space is communicated with the gas inlet of the combustion chamber so as to convey high-pressure gas to the combustion chamber for combustion to form high-temperature high-pressure gas, the gas outlet of the combustion chamber is communicated with the gas inlet of the volute, the high-temperature high-pressure gas after combustion is conveyed into the volute, the gas outlet of the volute is communicated with the gas inlet of the turbine, and the gas after combustion is conveyed to the turbine through the volute for doing work; due to the effect of the temperature difference between the inside and the outside of the volute, the volute can deform or move in the axial direction and/or the radial direction, and the volute and the casing are elastically connected in the axial direction and/or the radial direction, so that buffering can be provided for the deformation or the movement of the volute, the overall equivalent stress of the volute is reduced, and the service life of the volute is prolonged.

Optionally, the inner edge of the casing has an exhaust port along an axial direction, and at least part of the structure of the volute is located on an exhaust port opening side of the casing along the axial direction; the inner edge of the air outlet of the volute is in contact with the casing, and the outer edge of the air outlet of the volute is elastically connected with the corresponding edge of the air outlet of the casing along the axial direction.

Optionally, the gas turbine further comprises a C-shaped spring piece, wherein the C-shaped spring piece is annular and has a C-shaped cross section; an inner annular supporting wall is arranged at the outer edge of the air outlet of the volute, and extends outwards from the outer edge of the air outlet of the volute in the radial direction and is reversely bent to form a supporting surface; the C-shaped spring piece is elastically supported between the outer edge of the air outlet of the volute and the supporting surface, and has the same orientation as the air outlet of the volute, the outer edge of the C-shaped spring piece is fixedly connected with the outer edge of the air outlet of the volute, and the inner edge of the C-shaped spring piece is overlapped with the supporting surface.

Optionally, the supporting surface is provided with a clamping groove with an opening opposite to the opening of the C-shaped spring piece, the inner edge of the C-shaped spring piece is inserted into the clamping groove, and a gap is arranged between the inner edge of the C-shaped spring piece and the supporting surface.

Optionally, the volute comprises a volute body and a supporting ring, wherein the tail part of the volute body is located at the opening side of the exhaust port of the casing in the axial direction, and the opening direction of the volute body is opposite to the direction of the exhaust port of the casing; the inner edge of the opening of the volute body forms the outer edge of the air outlet of the volute, the inner edge of the supporting ring forms the inner edge of the air outlet of the volute, and the outer edge of the supporting ring is fixedly connected with the casing; the support ring is formed with a radially outward facing landing surface, and the outer edge of the opening of the volute body has a first bifurcation that overlaps the landing surface.

Optionally, an outer edge of the opening of the volute body has a second bifurcation, which at least partially overlaps the support ring in the axial direction.

Optionally, a gap is formed between the second bifurcation and the support ring.

Optionally, in the radial direction, the second bifurcated inner edge does not exceed the inner edge of the opening of the volute body.

Optionally, the gas turbine further comprises an annular inner supporting portion, the inner supporting portion is located on one side, away from the outer edge, of the inner edge of the supporting ring, the outer edge of the inner supporting portion is fixedly connected with the inner edge of the supporting ring, and the inner edge of the inner supporting portion is fixedly connected with the inner wall of the casing.

The utility model also discloses a vehicle, which comprises the gas turbine according to any one of the technical schemes.

The advantages of the vehicle over the prior art are the same as those of the gas turbine described above, and are not described in detail here.

Drawings

FIG. 1 is a schematic illustration of the general arrangement of a gas turbine volute and casing mating provided by an embodiment of the present utility model;

FIG. 2 is an axial schematic view of the volute of FIG. 1;

FIG. 3 is a schematic illustration of an arrangement of a volute body and a support ring in a gas turbine provided by an embodiment of the present utility model;

FIG. 4 is an enlarged partial schematic view of the vicinity of the C-shaped spring piece of FIG. 1;

fig. 5 is a schematic view of the support ring of fig. 1.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

FIG. 1 shows a cross-section of an assembly of a casing and a volute in a gas turbine, the complete structure of the assembly being in particular formed by a single revolution of the section about an axis L, the axis E being parallel to the axis L and the radial F being perpendicular to the axis L; any one of the above-described members has an inner edge at an end closer to the axis L in the radial direction F and an outer edge at an end farther from the axis L. In the embodiment of the utility model, "A and/or B" means A, B, or three schemes A and B.

In connection with fig. 1 to 5:

the gas turbine provided by the embodiment of the utility model comprises: the compressor, the casing 01, the volute 02, the combustion chamber and the turbine, which are not shown in the figure; the casing 01 specifically comprises a casing outer ring 1, a casing inner ring 2 and a combustion chamber casing 3 connected between the casing outer ring 1 and the right end of the casing inner ring 2, wherein the left end of the casing outer ring 1 and the left end of the casing inner ring 2 are sequentially connected through a primary guide supporting ring 10 and a diffuser ring 9. The inner casing ring 2 and the first-stage guide supporting ring 10 enclose an exhaust port N, and the diffuser ring 9 and the outer casing ring 1 enclose a diffuser outlet.

The volute 02 and the casing 01 are both annular, the volute 02 is located in the casing 01 and is coaxially arranged with the casing 01, for example, an axis L is taken as a central axis, an air outlet (see an outlet of a diffuser in fig. 1) of the air compressor is communicated with an air inlet of an interlayer space U, and the interlayer space U represents a space between the casing 01 and the volute 02 so that the air compressor can conveniently convey compressed high-pressure air into the interlayer space U; the gas outlet of the interlayer space U is communicated with the gas inlet of the combustion chamber to convey high-pressure gas to the combustion chamber for combustion to form high-temperature high-pressure gas, the gas outlet of the combustion chamber is communicated with the gas inlet of the volute 02, the high-temperature high-pressure gas after combustion is conveyed into the volute 02, the gas outlet M of the volute 02 is communicated with the gas inlet of the turbine, and the gas after combustion is conveyed to the turbine through the volute 02 for acting; due to the effect of the temperature difference between the inside and outside of the volute 02, the volute 02 can deform or move in the axial direction E and/or the radial direction F, and the volute 02 and the casing 01 are elastically connected in the axial direction E and/or the radial direction F, so that buffering can be provided for the deformation or the movement of the volute 02, the overall equivalent stress of the volute 02 is reduced, and the service life of the volute 02 is prolonged.

In a specific embodiment, the inner edge of the casing 01 has an exhaust port N along the axial direction E, at least part of the structure of the volute 02 is located on the opening side of the exhaust port N of the casing 01, for example, in fig. 1, the exhaust port N of the casing 01 is directed to the right, and the tail of the volute 02 is located on the right of the exhaust port N in the axial direction E, in which structure the temperature difference between the high-temperature gas inside the volute 02 and the cooling gas of the interlayer space U is formed on the volute 02, particularly the space between the part of the volute 02 located on the right of the exhaust port N and the casing 01; the air outlet M of the volute 02 is aligned with the air outlet N of the casing 01, and the inner edge of the air outlet M of the volute 02 contacts with the casing 01, so that the air outlet M of the volute 02 can only contact with the casing 01, or can be fixed to the casing 01, when the air outlet M of the volute 02 contacts with the casing 01 but is not fixed, a certain degree of freedom can be provided for the inner edge of the air outlet M of the volute 02, and when the volute 02 moves due to temperature difference, the problem that the inner edge of the air outlet M is pulled by the casing 01 can be relieved; the outer edge of the air outlet M of the volute 02 is elastically connected with the corresponding edge of the air outlet N of the casing 01 along the axial direction E, so that the internal thermal stress of the volute 02 is released at the elastic connection position, the elastic connection position can replace the whole volute 02 to finish the axial direction E deformation release at the position, and the thermal stress of the volute is reduced. To a certain extent, the above-mentioned elastic connection can also achieve a deformation release in the radial direction F.

The outer edge of the air outlet M of the volute 02 and the corresponding edge of the air outlet N of the casing 01 can be elastically connected in the axial direction E in various manners, specifically, the gas turbine further comprises a C-shaped spring piece 11, the C-shaped spring piece 11 has an annular structure surrounding the axial direction L, and a section cut along the radial direction F is C-shaped; the outer edge of the air outlet M of the volute 02 is provided with an inner annular supporting wall 5, the inner annular supporting wall 5 extends outwards from the outer edge of the air outlet M of the volute 02 along the radial direction F and is reversely bent to form a supporting surface S2, the supporting surface S2 faces towards the outer edge along the radial direction F, one end of the inner annular supporting wall 5 is fixedly connected with the outer edge of the air outlet M of the volute 02 and extends leftwards, then extends towards the outer edge and extends rightwards, the cross section of the inner annular supporting wall is of a U-shaped structure, and the side wall of the outer edge of the air outlet N of the casing 01, which is far away from the U-shaped structure, forms the supporting surface S2; the C-shaped spring piece 11 is elastically supported between the outer edge of the air outlet M of the volute 02 and the supporting surface S2, and has the same orientation as the air outlet M of the volute 02, the outer edge of the C-shaped spring piece 11 is fixedly connected with the outer edge of the air outlet M of the volute 02, specifically may be welded, and the inner edge of the C-shaped spring piece 11 is overlapped with the supporting surface S2, so that when the volute 02 moves along the axial direction F, the inner edge of the C-shaped spring piece 11 can move along the axial direction relative to the supporting surface S2, thereby releasing thermal stress. In addition, the C-shaped spring piece 11 bears high-temperature fuel gas in the volute 02 and cooling gas outside the volute 02, and the C-shaped spring piece not only releases the thermal stress in the volute 02 through deformation, but also can replace the integral volute 02 to complete deformation release of the axial F at the position, so that the thermal stress at the position of the volute is reduced. The C-shaped spring piece 11 can be arranged according to the structure, and the axial span is elongated as much as possible without affecting the assembly, and the thermal stress generated by the temperature difference caused by cold and hot air can be absorbed by the axial length. The axial span of the C-shaped spring piece 11 may be 1 to 5 times, more specifically 3 to 4 times, the radius of the arc of the C-shaped spring piece 11, avoiding that the axial span is too short, affecting the ability of the C-shaped spring piece 11 to absorb thermal stresses in the axial direction E.

Specifically, the outer edge of the exhaust port N of the casing 01 is provided with a primary guide 7, and the inner edge of the inner annular supporting wall 5 can be fixedly connected with the outer edge of the primary guide 7 through bolts.

In a specific embodiment, the support surface S2 has a slot with an opening opposite to the opening of the C-shaped spring piece 11, and the inner edge of the C-shaped spring piece 11 is inserted into the slot. Specifically, a clamping plate 51 may be fixed on the supporting surface S2, and the clamping plate 51 and the supporting surface S2 enclose the clamping groove, and an opening of the clamping groove faces the C-shaped spring piece 11 in the axial direction E, or the clamping groove and the opening of the C-shaped spring piece 11 are opposite and opposite to each other. The inner edge of the C-shaped spring piece 11 is inserted into the clamping groove along the axial direction E, and when the cooling gas in the interlayer space U flows from the bottom of the clamping groove to the opening side, the cooling gas cannot enter the clamping groove, and also cannot easily enter the gap between the C-shaped spring piece 11 and the supporting surface S2. Thus, while achieving an elastic connection of the C-shaped spring piece 11 with the support surface S2, the entry of cooling air into the scroll 02 is avoided at least to some extent.

One end of the clamping plate 51 far away from the clamping groove opening is welded and fixed with the supporting surface S2, and one end of the clamping plate 51 near the clamping groove opening can form an expanding part a which is bent towards one side far away from the supporting surface S2 so as to guide the inner edge of the C-shaped spring piece 11.

The edge of the inner edge of the C-shaped spring piece 11 is provided with a thickened section 111, the edge of the thickened section 111 facing the bottom of the clamping groove is provided with a guiding tip structure, guiding is facilitated during insertion, and a gap P is arranged between the part of the inner edge of the C-shaped spring piece 11 except for the thickened section 111 and the supporting surface S2 due to the fact that the part is lifted by the thickened section 111. The inner edge of the C-shaped spring piece 11 is not directly fixed to the support surface S2, and the clearance P provides a movable space for the inner edge of the C-shaped spring piece 11, so that the C-shaped spring piece 11 and the support surface S2 can be buffered conveniently.

In a specific embodiment, the volute 02 includes a volute body 4 and a supporting ring 6, the tail of the volute body 4 is located at the opening side of the exhaust port N of the casing 01 in the axial direction E, the tail of the volute body 4 may be fixed to the casing 01 by a plurality of fixing lugs 14 arranged at intervals in the circumferential direction, specifically the fixing lugs 14 may be sequentially and fixedly connected with the connecting lugs of the inner wall of the casing 01 by screws, the fixing positions of the fixing lugs 14 may be near the round corner positions of the outer edge of the tail of the volute body 4, four or other airflow holes 13 are uniformly arranged in the circumferential direction of the volute body 4 so that the interior of the volute 02 is communicated with the combustion chamber, and the opening direction of the volute body 4 is opposite to the direction of the exhaust port N of the casing 01, and the opening of the volute body 4 is located at the outer edge side of the exhaust port N of the casing 01, and the cooling gas in the gap between the inner edge of the volute body 4 and the inner edge of the casing 01 causes the reciprocating movement of the volute body 4 in the axial direction; the inner edge of the opening of the volute body 4 forms the outer edge of the air outlet M of the volute 02, the inner edge of the supporting ring 6 forms the inner edge of the air outlet M of the volute 02, and the outer edge of the supporting ring 6 is fixedly connected with the casing 01; the support ring 6 is formed with a joint surface S1 facing outward in the radial direction F, and the outer edge of the opening of the volute body 4 has a first bifurcation 41, and the first bifurcation 41 is lapped on the joint surface S1. The first bifurcation 41 of the volute body 4 and the supporting ring 6 cooperate to form a closed volute 02 space, and a certain gap can exist between the overlap surface S1 and the first bifurcation 41, so that the position of the volute 02 in the running state can be freely deformed in the radial direction E, and the axial direction E can mutually slide to replace the Leng Rela dragging effect of the integral volute at the position, thereby reducing the thermal stress of the volute.

Specifically, the outer edge of the supporting ring 6 is fixed on the volute thermal insulation plate 8 through bolts 15, the bolt holes on the volute thermal insulation plate 8 can be waist-shaped holes along the radial direction F, the outer ring 6 of the volute supporting ring can be allowed to expand radially, cold air vent holes 12 for circulating cooling air (dotted arrows) are circumferentially distributed near the outer edge and the inner edge of the supporting ring 6, and the cold air at the outlet of the diffuser is used for cooling the volute 02 through the integral outer ring of the volute 02.

Above, changed the structure of traditional whole spiral case, formed confined spiral case 02 through the concatenation mode, utilized the mosaic structure of C shape spring leaf 11 and first bifurcation 41, released spiral case 02 effectively because the thermal deformation that cold and hot difference brought, can improve spiral case 02 and bear the biggest difference in temperature, can bear higher combustion chamber outlet temperature, has positive effect to improving the whole quick-witted performance of gas turbine and spiral case 02's life.

In a specific embodiment, the outer edge of the opening of the volute body 4 is provided with a second bifurcation 42, and the second bifurcation 42 and the support ring 6 are at least partially overlapped, may be parallel to each other, and may form a shield for the fuel gas (implementing an arrow) after the combustion of the combustion chamber, so as to protect the support ring 6.

In a specific embodiment, a gap is formed between the second bifurcation 42 and the support ring 6, which ensures that the gap arrangement can effectively reduce the impact of high temperature fuel gas on the support ring 6 in a normal operation thermal state, further reducing the temperature of the support ring 6, and the gap also has a certain heat insulation effect.

In a particular embodiment, the inner edge of the second bifurcation 42 does not exceed the inner edge of the opening of the volute body 4 in the radial direction F. Too low an inner edge of the second bifurcation 42 will result in too low an overall temperature of the supporting ring 6, and small deformation of the radial direction E will cause too large a gap between the mating positions of the second bifurcation 42 and the supporting ring 6, causing the hot gas to flow backward, and the height of the radial direction F of the inner edge of the second bifurcation 42 is determined by the deformation of the volute body 4 and the supporting ring 6.

In a specific embodiment, the gas turbine further comprises an annular inner support portion 17, the inner support portion 17 is located on one side, away from the outer edge, of the inner edge of the support ring 6, the outer edge of the inner support portion 17 is fixedly connected with the inner edge of the support ring 6, and the inner edge of the inner support portion 17 is fixedly connected with the inner wall of the casing 01. Since the inner edge of the support ring 6 is abutted against the casing 01, the inner edge of the support ring 6 can move when impacted, and the inner edge of the support ring 6 is tightly matched and fixed between the primary guide support ring 10 and the diffuser ring 9 through the axial direction E and the radial direction F.

Based on the same inventive concept, the embodiment of the utility model also discloses a vehicle, which comprises the gas turbine provided by the embodiment, wherein the gas turbine is used for providing power output for the vehicle. The vehicle may be, but is not limited to, a ship and an aircraft. Reference is made to the gas turbine above for technical effects.

It will be apparent to those skilled in the art that various modifications and variations can be made to the embodiments of the present utility model without departing from the spirit and scope of the utility model. Thus, it is intended that the present utility model also include such modifications and alterations insofar as they come within the scope of the appended claims or the equivalents thereof.

Claims (10)

1. A gas turbine, comprising: the device comprises a compressor, a casing, a volute, a combustion chamber and a turbine;

the volute and the casing are annular, the volute is positioned in the casing and is coaxially arranged with the casing, an air outlet of the air compressor is communicated with an air inlet of an interlayer space, and the interlayer space represents a space between the casing and the volute; the air outlet of the interlayer space is communicated with the air inlet of the combustion chamber, the air outlet of the combustion chamber is communicated with the air inlet of the volute, and the air outlet of the volute is communicated with the air inlet of the turbine;

the volute is elastically connected with the casing along the axial direction and/or the radial direction.

2. The gas turbine of claim 1, wherein an inner edge of the casing has an exhaust port in an axial direction, along which at least a portion of the structure of the volute is located on an exhaust port opening side of the casing;

the inner edge of the air outlet of the volute is in contact with the casing, and the outer edge of the air outlet of the volute is elastically connected with the corresponding edge of the air outlet of the casing along the axial direction.

3. The gas turbine of claim 2, further comprising a C-shaped leaf spring, the C-shaped leaf spring being annular and C-shaped in cross section;

an inner annular supporting wall is arranged at the outer edge of the air outlet of the volute, and extends outwards from the outer edge of the air outlet of the volute in the radial direction and is reversely bent to form a supporting surface;

the C-shaped spring piece is elastically supported between the outer edge of the air outlet of the volute and the supporting surface, and has the same orientation as the air outlet of the volute, the outer edge of the C-shaped spring piece is fixedly connected with the outer edge of the air outlet of the volute, and the inner edge of the C-shaped spring piece is overlapped with the supporting surface.

4. A gas turbine according to claim 3, wherein the support surface has a slot with an opening opposite to the opening of the C-shaped spring plate, the inner edge of the C-shaped spring plate being inserted into the slot with a gap therebetween.

5. The gas turbine according to any one of claims 2 to 4, wherein the volute includes a volute body and a support ring, a tail portion of the volute body is located on an opening side of an exhaust port of the casing in the axial direction, and an opening direction of the volute body is opposite to an exhaust port direction of the casing;

the inner edge of the opening of the volute body forms the outer edge of the air outlet of the volute, the inner edge of the supporting ring forms the inner edge of the air outlet of the volute, and the outer edge of the supporting ring is fixedly connected with the casing;

the support ring is formed with a radially outward facing landing surface, and the outer edge of the opening of the volute body has a first bifurcation that overlaps the landing surface.

6. The gas turbine of claim 5, wherein an outer edge of the opening of the volute body has a second bifurcation that at least partially overlaps the support ring in the axial direction.

7. The gas turbine of claim 6, wherein a gap is formed between the second bifurcation and the support ring.

8. The gas turbine of claim 6, wherein the second bifurcated inner edge does not exceed an inner edge of the opening of the volute body in the radial direction.

9. The gas turbine of claim 5, further comprising an annular inner support portion located on a side of an inner edge of the support ring facing away from an outer edge, the outer edge of the inner support portion being fixedly connected to the inner edge of the support ring, the inner edge of the inner support portion being fixedly connected to an inner wall of the casing.

10. A vehicle comprising a gas turbine according to any one of claims 1 to 9.