Gas turbine and vehicle

Abstract

The present invention relates to the technical field of power devices, and discloses a gas turbine and a vehicle, wherein the gas turbine comprises: a compressor, a casing, a volute, a combustion chamber and a turbine; the volute and the casing are both annular, the volute is located in the casing and is coaxially arranged with the casing, the air outlet of the compressor is connected with the air inlet of the interlayer space, the interlayer space represents the space between the casing and the volute, so that the compressor can transport the compressed high-pressure gas into the interlayer space; the air outlet of the interlayer space is connected with the air inlet of the combustion chamber, the air outlet of the combustion chamber is connected with the air inlet of the volute, and the high-temperature and high-pressure gas after combustion is transported into the volute, the air outlet of the volute is connected with the air inlet of the turbine, and the combusted gas is then transported to the turbine through the volute to perform work; by elastically connecting the volute and the casing in the axial and / or radial directions, a buffer can be provided for the deformation or movement of the volute, the overall equivalent stress of the volute is reduced, and the service life of the volute is increased.

Description

Technical Field

[0001] The present invention relates to the technical field of power devices, and in particular to a gas turbine and a vehicle. Background Art

[0002] A gas turbine is an internal combustion engine that uses a continuously flowing gas as a working fluid to drive the rotation of an impeller, converting chemical energy into work. It consists of three core components: a compressor, a combustion chamber, and a gas turbine. The compressor compresses air into high-pressure air, which enters the combustion chamber and mixes with fuel to form high-temperature combustion gas. This high-temperature combustion gas enters the turbine, expands, and produces work, causing the turbine to rotate, driving the compressor and generator to rotate and generate electricity. The volute is the intermediate section connecting the combustion chamber and the gas turbine. The inlet is the combustion chamber outlet and has extremely high temperatures, reaching over 1100K. The inner edge of the outlet is cooled by the cooling air, reaching temperatures as high as 500K. The volute as a whole is subject to extremely high temperature differences, which directly affects its lifespan.

[0003] In recent years, in order to improve the performance of gas turbines, the temperature of the combustion chamber has been continuously increased, and the temperature difference of the volute has also been continuously increased. The traditional volute structure has a large limitation on the temperature difference. Summary of the Invention

[0004] The invention discloses a gas turbine and a vehicle, which are used to alleviate the restriction of the volute on the temperature difference and increase the service life of the volute.

[0005] To achieve the above object, the present invention provides the following technical solutions:

[0006] In a first aspect, a gas turbine is provided, comprising: a compressor, a casing, a volute, a combustion chamber and a turbine; the volute and the casing are both annular, the volute is located in the casing and is coaxially arranged with the casing, the air outlet of the compressor is connected to the air inlet of the interlayer space, the interlayer space represents the space between the casing and the volute, so that the compressor can transport the compressed high-pressure gas into the interlayer space; the air outlet of the interlayer space is connected to the air inlet of the combustion chamber to transport the high-pressure gas to the combustion chamber for combustion to form a high-pressure gas. The high-temperature and high-pressure gas is transmitted to the volute through the exhaust port of the combustion chamber, and the high-temperature and high-pressure gas after combustion is delivered to the volute. The outlet of the volute is connected to the air inlet of the turbine, and the combusted gas is then delivered to the turbine through the volute to perform work. Due to the temperature difference between the inside and outside of the volute, the volute will deform or move in the axial and / or radial directions. By elastically connecting the volute and the casing in the axial and / or radial directions, a buffer can be provided for the deformation or movement of the volute, thereby reducing the overall equivalent stress of the volute and improving the service life of the volute.

[0007] Optionally, the inner edge of the casing has an exhaust port along the axial direction, and along the axial direction, at least part of the structure of the volute is located on the opening side of the exhaust port of the casing; wherein, the air outlet of the volute is aligned with the exhaust port 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 to the corresponding edge of the exhaust port of the casing along the axial direction.

[0008] Optionally, the gas turbine further comprises a C-shaped spring sheet, which is annular and has a C-shaped cross-section; an outer edge of the air outlet of the volute is provided with an inner annular support wall, and the inner annular support wall extends radially outward from the outer edge of the air outlet of the volute and is bent in the opposite direction to form a support surface; the C-shaped spring sheet is elastically supported between the outer edge of the air outlet of the volute and the support surface, and has the same orientation as the air outlet of the volute, the outer edge of the C-shaped spring sheet is fixedly connected to the outer edge of the air outlet of the volute, and the inner edge of the C-shaped spring sheet overlaps the support surface.

[0009] Optionally, the support surface has a slot with an opening opposite to the opening of the C-shaped spring piece, and the inner edge of the C-shaped spring piece is inserted into the slot with a gap between it and the support surface.

[0010] Optionally, the volute includes a volute body and a support ring, the tail of the volute body is located on 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 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 support ring forms the inner edge of the air outlet of the volute, and the outer edge of the support ring is fixedly connected to the casing; the support ring is formed with a radially outward overlapping surface, and the outer edge of the opening of the volute body has a first fork, and the first fork overlaps the overlapping surface.

[0011] Optionally, the outer edge of the opening of the volute body has a second fork, and along the axial direction, the second fork at least partially overlaps with the support ring.

[0012] Optionally, a gap is formed between the second fork and the support ring.

[0013] Optionally, along the radial direction, an inner edge of the second fork does not exceed an inner edge of the opening of the volute body.

[0014] Optionally, the gas turbine further includes an annular inner support portion, which is located on the side of the inner edge of the support ring away from the outer edge, the outer edge of the inner support portion is fixedly connected to the inner edge of the support ring, and the inner edge of the inner support portion is fixedly connected to the inner wall of the casing.

[0015] The present invention also discloses a vehicle, which includes the gas turbine described in any of the above technical solutions.

[0016] The advantages of the vehicle described above are the same as those of the gas turbine described above over the prior art, which will not be described in detail here. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 A schematic diagram of the overall arrangement of the volute and casing of a gas turbine provided in an embodiment of the present application;

[0018] Figure 2 for Figure 1 Axial schematic diagram of the volute in;

[0019] Figure 3 A schematic diagram of the arrangement of the volute body and the support ring in the gas turbine provided in an embodiment of the present application;

[0020] Figure 4 for Figure 1 A partial enlarged schematic diagram of the vicinity of the C-shaped spring piece;

[0021] Figure 5 for Figure 1 Schematic diagram of the support ring in. DETAILED DESCRIPTION

[0022] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0023] Figure 1 A cross-sectional view of the assembly formed by the casing and volute in a gas turbine is shown. The complete structure of the assembly is formed by rotating the cross-section around axis L. The axial direction E is parallel to axis L, and the radial direction F is perpendicular to axis L. For any component in the cross-section, the end closest to axis L along radial direction F is the inner edge, and the end farther from axis L is the outer edge. In the embodiments of the present application, "A and / or B" refers to options A, B, or both A and B.

[0024] Combine Figures 1 to 5 :

[0025] The gas turbine provided in the embodiment of the present application includes: a compressor, a casing 01, a volute 02, a combustion chamber, and a turbine. The compressor, combustion chamber, and turbine are not shown in the figure. The casing 01 specifically includes a casing outer ring 1, a casing inner ring 2, and a combustion chamber casing 3 connected between the right ends of the casing outer ring 1 and the casing inner ring 2. The left end of the casing outer ring 1 and the left end of the casing inner ring 2 are connected in sequence through a first-stage guide support ring 10 and a diffuser ring 9. The casing inner ring 2 and the first-stage guide support ring 10 form an exhaust port N, and the diffuser ring 9 and the casing outer ring 1 form a diffuser outlet.

[0026] The volute 02 and the casing 01 are both annular, and the volute 02 is located inside the casing 01 and is coaxial with the casing 01. For example, the volute 02 and the casing 01 are both located coaxially with the axis L as the central axis. Figure 1 The middle diffuser outlet) is connected to the air inlet of the interlayer space U, and the interlayer space U represents the space between the casing 01 and the volute 02, so that the compressor can transport the compressed high-pressure gas into the interlayer space U; the air outlet of the interlayer space U is connected to the air inlet of the combustion chamber to transport the high-pressure gas to the combustion chamber for combustion to form high-temperature and high-pressure gas, and the air outlet of the combustion chamber is connected to the air inlet of the volute 02 to transport the high-temperature and high-pressure combustion gas into the volute 02, and the air outlet M of the volute 02 is connected to the air inlet of the turbine, and the combustion gas is then transported to the turbine through the volute 02 to do work; due to the temperature difference between the inside and outside of the volute 02, the volute 02 will deform or move in the axial direction E and / or radial direction F, and by elastically connecting the volute 02 and the casing 01 along the axial direction E and / or radial direction F, a buffer can be provided for the deformation or movement of the volute 02, the overall equivalent stress of the volute 02 is reduced, and the service life of the volute 02 is increased.

[0027] In a specific embodiment, the inner edge of the casing 01 has an exhaust port N along the axial direction E. 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, Figure 1In the embodiment, the exhaust port N of the casing 01 faces rightward, and the tail of the volute 02 is located to the right of the exhaust port N in the axial direction E. In this structure, the temperature difference between the high-temperature combustion gas inside the volute 02 and the cooling gas in the interlayer space U causes a temperature difference in the volute 02, especially in the space between the portion of the volute 02 located to the right of the exhaust port N and the casing 01; wherein, the air outlet M of the volute 02 is aligned with the exhaust port N of the casing 01, and the inner edge of the air outlet M of the volute 02 contacts the casing 01, and may only abut against the casing 01, or may be fixed to the casing 01. 1. When the air outlet M of the volute 02 is in contact with the casing 01 but not fixed, a certain degree of freedom can be provided for the inner edge of the air outlet M of the volute 02. When the volute 02 moves due to a temperature difference, the problem of the inner edge of the air outlet M being pulled by the casing 01 can be alleviated. The outer edge of the air outlet M of the volute 02 is elastically connected to the corresponding edge of the exhaust port N of the casing 01 along the axial direction E, so that the volute 02 can release internal thermal stress at the elastic connection. The elastic connection can replace the volute 02 as a whole to complete the axial deformation release E at this location, reducing the thermal stress of the volute at this location. To a certain extent, the above-mentioned elastic connection can also achieve deformation release in the radial direction F.

[0028] There are many ways to elastically connect the outer edge of the air outlet M of the volute 02 and the corresponding edge of the exhaust port N of the casing 01 along the axial direction E. Specifically, the gas turbine further includes a C-shaped spring sheet 11, which is an annular structure surrounding the axial direction L, and the cross 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 support wall 5, and the inner annular support wall 5 extends outward 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 support surface S2, and the support surface S2 faces the outer edge along the radial direction F. One end of the inner annular support wall 5 is fixedly connected to the outer edge of the air outlet M of the volute 02, and extends to the left, and then to The outer edge extends and then extends to the right side, with a U-shaped cross-section. The side wall of the U-shaped structure away from the outer edge of the exhaust port N of the casing 01 forms the above-mentioned support 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 support 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 to the outer edge of the air outlet M of the volute 02, which can be specifically welded, and the inner edge of the C-shaped spring piece 11 overlaps the support 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 axially relative to the support surface S2, thereby releasing thermal stress. In addition, the C-shaped spring piece 11 withstands the high-temperature combustion gas inside the volute 02 and the cooling gas outside the volute 02. The C-shaped spring piece not only releases the internal thermal stress of the volute 02 through deformation, but also can replace the entire volute 02 to complete the axial deformation release F at this location, reducing the thermal stress of the volute at this location. The C-shaped spring leaf 11 can be arranged in a structural manner so that its axial span is as long as possible without affecting assembly, thereby maximizing its axial length to absorb the thermal stress generated by the temperature difference between hot and cold air. The axial span of the C-shaped spring leaf 11 can be 1 to 5 times the radius of the circular arc of the C-shaped spring leaf 11, more specifically 3 to 4 times, to avoid an axial span that is too short and affects the ability of the C-shaped spring leaf 11 to absorb thermal stress in the axial direction E.

[0029] Specifically, a primary guide 7 is provided at the outer edge of the exhaust port N of the casing 01 , and the inner edge of the inner annular support wall 5 can be fixedly connected to the outer edge of the primary guide 7 by bolts.

[0030] In a specific embodiment, the support surface S2 has a slot with an opening opposite to the opening of the C-shaped spring sheet 11, and the inner edge of the C-shaped spring sheet 11 is inserted into the slot. Specifically, a card plate 51 can be fixed to the support surface S2, and the card plate 51 and the support surface S2 form the above-mentioned slot. The opening of the slot is oriented toward the C-shaped spring sheet 11 in the axial direction E, or in other words, the slot is opposite to the opening direction of the C-shaped spring sheet 11 and is arranged relative to each other. The inner edge of the C-shaped spring sheet 11 is inserted into the above-mentioned slot along the axial direction E. When the cooling air in the interlayer space U flows from the bottom of the slot to the opening side, it cannot enter the slot, nor does it easily enter the gap between the C-shaped spring sheet 11 and the support surface S2. Thus, while achieving an elastic connection between the C-shaped spring sheet 11 and the support surface S2, the cooling air is prevented from entering the volute 02 to a certain extent.

[0031] The end of the clamping plate 51 away from the slot opening is welded and fixed to the support surface S2. The end of the clamping plate 51 close to the slot opening can form an expansion portion a bent toward the side away from the support surface S2 to guide the inner edge of the C-shaped spring piece 11.

[0032] 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 slot is formed with a guide tip structure to facilitate guidance during insertion. The inner edge of the C-shaped spring piece 11, excluding the thickened section 111, is raised by the thickened section 111, and a gap P is provided between the inner edge and the support surface S2. The inner edge of the C-shaped spring piece 11 is not directly fixed to the support surface S2. At the same time, the above-mentioned gap P provides space for the inner edge of the C-shaped spring piece 11 to move, facilitating a buffer between the C-shaped spring piece 11 and the support surface S2.

[0033] In a specific embodiment, the volute 02 includes a volute body 4 and a support ring 6. The tail of the volute body 4 is located on the opening side of the exhaust port N of the casing 01 in the axial direction E. The tail of the volute body 4 can be fixed to the casing 01 by a plurality of fixing ears 14 arranged at intervals in the circumferential direction. Specifically, the fixing ears 14 can be fixedly connected to the connecting ears on the inner wall of the casing 01 in sequence by screws. The fixing position of the fixing ears 14 can be close to the rounded position of the outer edge of the tail of the volute body 4. Four or other number of air flow holes 13 are evenly arranged circumferentially on the volute body 4 to facilitate communication between the interior of the volute 02 and the combustion chamber, and the opening of the volute body 4 The direction is opposite to the exhaust port N of the casing 01. The opening of the volute main body 4 is located on the outer edge side of the exhaust port N of the casing 01. The cooling air in the gap between the inner edge of the volute main body 4 and the inner edge of the casing 01 will cause the volute main body 4 to reciprocate in the axial direction; the inner edge of the opening of the volute main body 4 forms the outer edge of the air outlet M of the volute 02, and the inner edge of the support ring 6 forms the inner edge of the air outlet M of the volute 02, and the outer edge of the support ring 6 is fixedly connected to the casing 01; the support ring 6 is formed with a lap surface S1 facing outward along the radial direction F, and the outer edge of the opening of the volute main body 4 has a first fork 41, and the first fork 41 overlaps the lap surface S1. The first fork 41 of the volute body 4 cooperates with the support ring 6 to form a closed volute 02 space. A certain gap is allowed to exist between the overlapping surface S1 and the first fork 41, which not only enables the volute 02 at this position to deform freely in the radial direction E under the running state, but also enables it to slide against each other through the axial direction E, replacing the hot and cold pulling effect of the integral volute at this location, thereby reducing the thermal stress of the volute.

[0034] Specifically, the outer edge of the support ring 6 is fixed to the volute heat insulation plate 8 by bolts 15. The bolt holes on the volute heat insulation plate 8 can be waist-shaped holes along the radial direction F, which can allow the volute support ring outer ring 6 to expand radially. Cold air vents 12 for the circulation of cooling air (dashed arrows) are arranged circumferentially near the outer edge and inner edge of the support ring 6. The cold air at the diffuser outlet passes through the overall outer ring of the volute 02 to cool the volute 02.

[0035] As described above, the structure of the traditional integral volute is changed, and a closed volute 02 is formed by splicing. The splicing structure of the C-shaped spring sheet 11 and the first fork 41 is utilized to effectively release the thermal deformation of the volute 02 caused by the hot and cold temperature difference, thereby increasing the maximum temperature difference that the volute 02 can withstand and can withstand a higher combustion chamber outlet temperature, which has a positive effect on improving the overall performance of the gas turbine and the service life of the volute 02.

[0036] In a specific embodiment, the outer edge of the opening of the volute body 4 has a second fork 42. Along the axial direction E, the second fork 42 at least partially overlaps with the support ring 6 and can be parallel to each other, which can block the post-combustion gas in the combustion chamber (as shown by the arrow) and protect the support ring 6.

[0037] In a specific embodiment, a gap is formed between the second fork 42 and the support ring 6. The gap ensures that under normal operating hot state, the gap arrangement can effectively reduce the impact of high-temperature gas on the support ring 6, further reducing the temperature of the support ring 6. The gap also has a certain heat insulation effect.

[0038] In a specific embodiment, the inner edge of the second fork 42 does not exceed the inner edge of the opening of the volute body 4 along the radial direction F. If the inner edge of the second fork 42 is too low, the overall temperature of the support ring 6 will be too low. A small deformation in the radial direction E will cause a large gap between the second fork 42 and the support ring 6, leading to hot gas backflow. The height of the inner edge of the second fork 42 in the radial direction F is determined by the deformation of the volute body 4 and the support ring 6.

[0039] In one specific embodiment, the gas turbine further includes an annular inner support portion 17, located on the inner edge of the support ring 6, facing away from the outer edge. The outer edge of the inner support portion 17 is fixedly connected to the inner edge of the support ring 6, and the inner edge of the inner support portion 17 is fixedly connected to the inner wall of the casing 01. Because the inner edge of the support ring 6 abuts the casing 01, the inner edge of the support ring 6 can move when impacted. The inner edge of the support ring 6 is tightly secured between the first-stage guide ring 10 and the diffuser ring 9 via axial and radial fits (E and F).

[0040] Based on the same inventive concept, embodiments of the present application also disclose a vehicle comprising the gas turbine provided in the aforementioned embodiments, which is configured to provide power output for the vehicle. The vehicle may include, but is not limited to, a ship or an aircraft. The technical effects thereof may be referenced to those of the gas turbine described above.

[0041] Obviously, those skilled in the art may make various changes and modifications to the embodiments of the present invention without departing from the spirit and scope of the present invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims and their equivalents, the present invention is intended to include such modifications and variations.

Claims

1. A gas turbine, characterized in that: include: compressor, casing, volute, combustion chamber and turbine; The volute and the casing are both annular in shape, the volute is located inside the casing and is coaxially arranged with the casing, the air outlet of the compressor is communicated with the air inlet of the interlayer space, and the interlayer space represents the 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 and the casing are elastically connected in the axial and / or radial directions; The inner edge of the casing has an exhaust port in an axial direction, and at least a portion of the volute is located on the exhaust port opening side of the casing in the axial direction; The air outlet of the volute is aligned with the exhaust port of the casing, the inner edge of the air outlet of the volute contacts the casing, and the outer edge of the air outlet of the volute is elastically connected to the corresponding edge of the exhaust port of the casing along the axial direction; The gas turbine further comprises a C-shaped spring sheet, the C-shaped spring sheet being annular and having a C-shaped cross section; An inner annular support wall is provided on the outer edge of the air outlet of the volute, and the inner annular support wall extends radially outward from the outer edge of the air outlet of the volute and bends in the opposite direction to form a support surface; The C-shaped spring piece is elastically supported between the outer edge of the air outlet of the volute and the support 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 to the outer edge of the air outlet of the volute, and the inner edge of the C-shaped spring piece overlaps the support surface. The support surface has a slot with an opening opposite to the opening of the C-shaped spring piece, and the inner edge of the C-shaped spring piece is inserted into the slot with a gap between the inner edge and the support surface; The volute includes a volute body and a support ring, the tail portion of the volute body is located on 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 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 support ring forms the inner edge of the air outlet of the volute, and the outer edge of the support ring is fixedly connected to the casing; the support ring is formed with a radially outward overlapping surface, and the outer edge of the opening of the volute body has a first fork, and the first fork overlaps the overlapping surface; The outer edge of the opening of the volute body has a second fork, and along the axial direction, the second fork at least partially overlaps with the support ring; A gap is formed between the second fork and the support ring; Along the radial direction, an inner edge of the second fork does not exceed an inner edge of the opening of the volute body.

2. The gas turbine according to claim 1, characterized in that The gas turbine also includes an annular inner support portion, which is located on the side of the inner edge of the support ring away from the outer edge. The outer edge of the inner support portion is fixedly connected to the inner edge of the support ring, and the inner edge of the inner support portion is fixedly connected to the inner wall of the casing.

3. A means of transport, characterized in that: Including the gas turbine according to claim 1 or 2.

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