CN114151194A - Double-layer force transmission device of gas turbine - Google Patents
Double-layer force transmission device of gas turbine Download PDFInfo
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- CN114151194A CN114151194A CN202210123139.XA CN202210123139A CN114151194A CN 114151194 A CN114151194 A CN 114151194A CN 202210123139 A CN202210123139 A CN 202210123139A CN 114151194 A CN114151194 A CN 114151194A
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- plate
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- baffle
- inclined plate
- gas turbine
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
Abstract
The invention discloses a double-layer force transmission device of a gas turbine, which comprises a first component, a second component and a third component, wherein the second component comprises an upper part and a lower part, the upper part and the first component form a Z-shaped structure, and the lower part and the third component form a herringbone structure; two sides of the Z-shaped structure are respectively provided with a baffle, the first component, the second component and the baffle enclose an air guide cavity, correspondingly, the upper part is provided with an air guide hole communicated with the air guide cavity, and the first component is provided with an air outlet communicated with the air guide cavity. The double-layer force transmission device of the gas turbine sequentially forms a Z-shaped structure and a human-shaped structure from top to bottom, the action direction of the action force is adjusted, the transmission of the action force is more uniform, and the deformation caused by uneven stress is reduced. Through the mutual cooperation of the Z-shaped structure and the baffle, heat is guided to be discharged, a temperature buffer area is formed, thermal deformation is reduced, and damage caused by the thermal deformation is reduced.
Description
Technical Field
The invention belongs to the technical field of force transmission structures, and particularly relates to a double-layer force transmission device of a gas turbine.
Background
The compressor is a component which uses blades rotating at high speed to do work on air in a gas turbine engine so as to improve the air pressure, the front end part of the blades of an impeller of the compressor is bent and called a guide wheel, and the front end part of the blades of the impeller of the compressor plays a role of guiding air into a working impeller without impact so as to reduce the impact loss of air flow. The outlet of the impeller of the compressor is provided with a diffuser, so that the kinetic energy obtained by the gas in the impeller is converted into pressure as much as possible.
The gas turbine compressor works under the working condition of high-speed rotation, so that an intermediate supporting device generally used at the joint of the high-pressure compressor and the low-pressure compressor plays a vital role. The main function of the intermediate support device is to connect the high-pressure compressor and the low-pressure compressor into a whole, and a reliable and stable working environment is needed to be ensured when the rotor rotates.
The existing gas turbine intermediate support device can generally meet the requirement of stable operation. But there are also certain disadvantages:
1) the temperature of the working environment of the compressor is high, so that part of components can generate certain deformation in the working process.
2) In terms of stress, the high-pressure compressor and the low-pressure compressor are stressed unevenly on the middle supporting part due to different working conditions and weights.
If the problems develop to an uncontrollable condition, the gas turbine can be damaged irreversibly, so that the engine vibrates and parts are scrapped if the problems are light, and a complete machine is seriously damaged if the problems are heavy. Therefore, if the above problems can be effectively optimized, the reliability and safety of the gas turbine can be greatly improved.
Disclosure of Invention
The invention aims to provide a double-layer force transmission device of a gas turbine, which solves the problems of thermal deformation and stress deformation of the traditional gas turbine middle supporting device.
In order to achieve the purpose, the invention adopts the following technical scheme:
a double-layer force transmission device of a gas turbine comprises a first component, a second component and a third component, wherein the second component comprises an upper part and a lower part, the upper part and the first component form a Z-shaped structure, and the lower part and the third component form a herringbone structure;
two sides of the Z-shaped structure are respectively provided with a baffle, the first component, the second component and the baffle enclose an air guide cavity, correspondingly, the upper part is provided with an air guide hole communicated with the air guide cavity, and the first component is provided with an air outlet communicated with the air guide cavity.
In one possible design, the first member includes a horizontal plate and a first inclined plate, wherein the air outlet is located on the horizontal plate, and one end of the horizontal plate is a free end, the other end of the horizontal plate is a connecting end, the high end of the first inclined plate is connected to the connecting end of the horizontal plate, and the low end of the first inclined plate is gradually inclined toward the free end of the horizontal plate and connected to the upper portion.
In one possible design, the baffle includes a first baffle and a second baffle;
the first baffle plate is provided with an inwards concave groove body, the upper end of the first baffle plate is connected with the free end of the horizontal plate, and the lower end of the first baffle plate is connected with the upper part;
the second baffle is an inwards concave arc plate, the upper end of the second baffle is connected with the connecting end of the horizontal plate, and the lower end of the second baffle is connected with the upper part.
In a possible design, from top to bottom, first baffle includes consecutive first riser, first hang plate, second riser, second hang plate and third riser, and wherein, the free end of horizontal plate is connected to the first riser, and upper portion is connected to the third riser, and correspondingly, the cell body of indent comprises first hang plate, second riser and second hang plate.
In one possible design, the second component comprises a flow channel part and a second inclined plate which are sequentially connected from bottom to top, wherein the flow channel part and the first component form a Z-shaped structure, and the second inclined plate and the third component form a herringbone structure;
runner portion and second swash plate all incline to set up, and the upper end of second swash plate is connected in the low side of runner portion, and the lower extreme of second swash plate inclines gradually to keeping away from runner portion direction.
In a possible design, a cavity which is adapted to a flow passage of the gas engine is arranged in the flow passage part, and the air-entraining holes are positioned on the side wall of the cavity.
In one possible design, the third component includes a third inclined plate, an upper end of the third inclined plate is connected with the high end of the flow channel part, and a lower end of the third inclined plate is gradually inclined towards a direction away from the flow channel part, so that an extension line of the third inclined plate and an extension line of the second inclined plate can intersect above the third inclined plate and the second inclined plate.
In one possible design, the included angle between the second inclined plate and the third inclined plate is within 42.5-45.5 degrees;
the included angle between the second inclined plate and the horizontal direction is 60 degrees +/-1 degree, and the included angle between the third inclined plate and the horizontal direction is 76 degrees +/-30 degrees.
Has the advantages that:
this double-deck power transmission device of gas turbine has formed "Z" word structure and "people" word structure from top to bottom in proper order through first part, second part and the mutual cooperation of third part, adjusts the effect direction of action of force, has improved holistic mechanical properties, makes the transmission of action of force more even, has reduced because the deformation that the atress inequality leads to.
Secondly, the Z-shaped structure is matched with the baffle plate, so that heat is guided to be discharged, a temperature buffer area is formed, thermal deformation is reduced, and damage caused by thermal deformation is reduced; meanwhile, the device has an isolation effect on external air and reduces the deformation of a cold-hot intersection.
And finally, the Z-shaped structure and the herringbone structure are matched with each other, so that the stability of the double-layer force transmission device of the gas turbine is improved, the gas turbine is ensured to be in a reliable and stable working environment, and the use safety and reliability of the gas turbine are improved.
Drawings
Fig. 1 is a schematic structural diagram of a double-layer force transmission device of a gas turbine.
In the figure:
1. a first member; 11. a horizontal plate; 12. a first sloping plate; 101. an air outlet; 2. a second component; 21. a flow channel part; 22. a second swash plate; 201. an air vent; 3. a third component; 31. a third sloping plate; 41. a first baffle plate; 411. a first vertical plate; 412. a first inclined plate; 413. a second vertical plate; 414. a second inclined plate; 415. a third vertical plate; 42. a second baffle.
Detailed Description
Example (b):
the existing supporting device for the gas turbine meets the requirement of stable work, but the heating deformation and the stress uneven deformation which are suffered in the working process are inevitable, but the existing supporting device lacks corresponding processing structures for the two kinds of deformation, so that the accumulated deformation after long-term use can make the supporting device difficult to realize the function of stable work, the normal work of the gas turbine is influenced, and even the gas turbine is damaged and destroyed.
Therefore, a supporting device capable of coping with the two types of deformation is provided, and particularly, as shown in fig. 1, a double-layer force transmission device of a gas turbine comprises a first component 1, a second component 2 and a third component 3, wherein the second component 2 comprises an upper part and a lower part, the upper part and the first component 1 form a Z-shaped structure, and the lower part and the third component 3 form a herringbone structure; two sides of the Z-shaped structure are respectively provided with a baffle, the first component 1, the second component 2 and the baffles enclose an air guide cavity, correspondingly, the upper part is provided with an air guide hole 201 communicated with the air guide cavity, and the first component 1 is provided with an air outlet 101 communicated with the air guide cavity.
When the gas turbine works, a certain amount of heat is generated and dissipated outwards, but the contact conditions of each part and the gas turbine are different, for example, the distance and the position are different, and the parts are in a non-uniform heating state, so that the parts are deformed to different degrees. Obviously, excessive deformation may destroy the stable operation of the gas turbine. Therefore, the damage caused by thermal deformation is relieved and reduced through the Z-shaped structure, namely the problem of thermal deformation is solved.
Furthermore, the Z-shaped structure and the baffle are matched with each other to form an air guide cavity, the air guide cavity isolates external air to prevent external low-temperature air from flowing into a working system, and deformation of cold and hot intersection positions is reduced. Meanwhile, the gas guide cavity is relatively sealed, the high-temperature gas is gradually cooled in the upward flowing process, the gas guide cavity can be divided into a plurality of temperature layers with gradually increased temperatures from bottom to top, and the gas guide cavity is changed into a temperature buffer area under the action of the heat of the gas turbine, so that the temperature of surrounding parts is balanced, and the thermal deformation is reduced. Meanwhile, the high-temperature gas is fully mixed and reaches a relatively uniform state in the flowing process in the gas guide cavity, and subsequent use is facilitated.
The problem of uneven stress is that the supporting device needs to be connected with the high-pressure compressor and the low-pressure compressor at the same time, the double-layer force transmission device of the gas turbine realizes the connection effect through a herringbone structure, the herringbone structure is provided with two support legs, and the lower ends of the two support legs are respectively connected with the high-pressure compressor and the low-pressure compressor, which is shown in figure 1. When the acting force is transmitted to the herringbone structure, the acting direction of the acting force is adjusted by the herringbone structure, the condition of uneven force transmission is improved, and the deformation caused by uneven stress is reduced. In addition, the shape of the herringbone structure is similar to a triangle, the stability of the herringbone structure is good, and the stability of the whole working system is improved.
Specifically, the working system, i.e. the system using the gas turbine double-layer force transmission device, includes, but is not limited to, the following components: a gas turbine, a high pressure compressor and a low pressure compressor.
Meanwhile, the double-layer force transmission device of the gas turbine consists of a plurality of parts, and when the double-layer force transmission device is maintained after being used for a long time, only damaged parts can be replaced, so that the replaceability is improved, the replacement cost of parts is also reduced, and the maintainability of the double-layer force transmission device of the gas turbine is improved.
The resistance to deformation will be further described below with reference to the specific structure of the double-layer force transfer device of the gas turbine:
in this embodiment, the first member 1 includes a horizontal plate 11 and a first inclined plate 12, wherein the air outlet 101 is located on the horizontal plate 11, one end of the horizontal plate 11 is a free end, the other end of the horizontal plate 11 is a connection end, a high end of the first inclined plate 12 is connected to the connection end of the horizontal plate 11, and a low end of the first inclined plate 12 is gradually inclined toward the free end of the horizontal plate 11 and connected to an upper portion.
That is, the first component 1 includes a part except the lowest plate body in a Z-shaped structure, wherein the upper part of the horizontal plate 11 can be connected with the corresponding component, and a person skilled in the art can select the type of the specific component according to the work requirement; the inclination angle of the first swash plate 12 is determined according to a specific installation space and working requirements.
Meanwhile, the horizontal plate 11 can bear a certain load, and the first inclined plate 12 can also adjust the action direction of the acting force, so that the first component 1 can be matched with a herringbone structure for use, namely the Z-shaped structure also has the function of adjusting the acting force.
The baffle plate is matched with the first component 1, so that the acting force is adjusted, meanwhile, the thermal deformation can be relieved, and the thermal damage is reduced, and particularly, the baffle plate comprises a first baffle plate 41 and a second baffle plate 42; an inwards concave groove body is arranged on the first baffle plate 41, the upper end of the first baffle plate 41 is connected with the free end of the horizontal plate 11, and the lower end of the first baffle plate 41 is connected with the upper part; the second baffle 42 is a concave arc plate, the upper end of the second baffle 42 is connected with the connecting end of the horizontal plate 11, and the lower end of the second baffle 42 is connected with the upper part.
I.e. the first and second baffles 41 and 42 on either side of the first element 1, are of different configurations and, in combination with practical use, heat flows through the upper portion of the second element 2, i.e. through the cavity of the gate 21, through the bleed holes 201 into the gas guide chamber and finally out of the gas turbine through the gas outlet 101.
In a possible implementation manner, referring to fig. 1, from top to bottom, the first baffle 41 includes a first vertical plate 411, a first inclined plate 412, a second vertical plate 413, a second inclined plate 414 and a third vertical plate 415 connected in sequence, where the first vertical plate 411 is connected to the free end of the horizontal plate 11, the third vertical plate 415 is connected to the upper portion, and accordingly, the concave groove body is composed of the first inclined plate 412, the second vertical plate 413 and the second inclined plate 414.
In one possible implementation, the curvature of the second baffle 42 is an arc with a radius of 115 and 125 cm; alternatively, the curvature of the second baffle 42 includes, but is not limited to, arcs of 115 centimeters, 117.5 centimeters, 120 centimeters, 122.5 centimeters, and 125 centimeters.
In this embodiment, the second component 2 includes a flow channel portion 21 and a second inclined plate 22 connected in sequence from bottom to top, wherein the flow channel portion 21 and the first component 1 form a "Z" structure, and the second inclined plate 22 and the third component 3 form a "herringbone" structure; runner portion 21 and second swash plate 22 all incline to set up, and the upper end of second swash plate 22 is connected in the low side of runner portion 21, and the lower extreme of second swash plate 22 inclines gradually to keeping away from runner portion 21 direction.
In combination with the above, the heat of the gas turbine will flow through the flow channel part 21, i.e. the flow channel part 21 guides the heat, and the heat is relieved through the "Z" shaped structure, i.e. the upper half of the double-layer force transfer device of the gas turbine, therefore the part of the flow channel part 21 located below the flow channel is made of heat insulating material to reduce the influence of the heat on the lower half of the double-layer force transfer device of the gas turbine.
The second inclined plate 22 is matched with the third component 3 to adjust the direction of the acting force, and the second inclined plate 22 is far away from the third component 3 from top to bottom to form a herringbone structure.
Obviously, the double-layer force transmission device of the gas turbine is used in cooperation with the gas turbine, so that when a flow passage of the gas turbine passes through the double-layer force transmission device of the gas turbine, a cavity communicated with the flow passage needs to be arranged, namely, a cavity adapted to the flow passage of the gas turbine is arranged in the flow passage part 21, and the air introducing hole 201 is arranged on the side wall of the cavity.
High-temperature gas flows through the flow channel, the high-temperature gas thermally deforms surrounding parts, and in order to avoid excessive deformation of the cavity, the cavity is provided with a gas introducing hole 201, so that heat is led out. Meanwhile, the appearance of the bleed holes 201 also enables the runner portion 21 to have a deformable space, so that the runner portion 21 is prevented from being broken due to expansion caused by heat and contraction caused by cold.
The heat guided out by the air guide holes 201 is guided into the air guide cavity and flows out of the air guide cavity, so that the temperature of the air guide cavity gradually rises from bottom to top, a temperature buffer zone is formed, and thermal deformation of surrounding parts is favorably adjusted. Optionally, the shape, number and position of the bleed air holes 201 are selected and combined by a person skilled in the art according to the actual conditions of use.
In the present embodiment, the third member 3 includes a third inclined plate 31, an upper end of the third inclined plate 31 is connected to the high end of the flow path portion 21, and a lower end of the third inclined plate 31 is gradually inclined in a direction away from the flow path portion 21, so that an extension line of the third inclined plate 31 may intersect with an extension line of the second inclined plate 22 above the same.
Now, with reference to the structures of the second member 2 and the third member 3, the deformation caused by uneven stress is relieved, when an acting force is applied to the herringbone structure, the acting force can be decomposed into a vertical component and a horizontal component, and referring to fig. 1, from bottom to top, the second inclined plate 22 and the third inclined plate 31 are close to each other, the directions of the decomposed horizontal components are opposite, the horizontal components are offset with each other, and the absolute value of the whole acting force is reduced. Therefore, the mechanical property of the herringbone structure is improved, the force transmission is more uniform, and the reliability and the safety of the gas turbine are improved.
In one possible implementation, the included angle between the second inclined plate 22 and the third inclined plate 31 is within 42.5 ° to 45.5 °; the included angle between the second inclined plate 22 and the horizontal direction is 60 degrees +/-1 degree, and the included angle between the third inclined plate 31 and the horizontal direction is 76 degrees +/-30 degrees.
Optionally, the included angle between the second sloping plate 22 and the third sloping plate 31 includes, but is not limited to, 42.5 °, 43 °, 43.5 °, 44 °, 44.5 °, 45 ° and 45.5 °, the included angle between the second sloping plate 22 and the horizontal direction includes, but is not limited to, 59 °, 59.5 °, 60 °, 60.5 ° and 61 °, and the included angle between the third sloping plate 31 and the horizontal direction includes, but is not limited to, 75.5 °, 76 ° and 76.5 °.
It is easy to understand that on the basis that the included angle between the second inclined plate 22 and the third inclined plate 31 is within 42.5 degrees to 45.5 degrees, the included angle between the second inclined plate 22 and the horizontal direction and the included angle between the second inclined plate 22 and the horizontal direction can be adjusted at will.
The included angle is adapted to the type of the gas turbine used, and those skilled in the art can increase or decrease the included angle appropriately according to the actual type of the gas turbine, which is not described herein again.
Finally, it should be noted that: the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. The double-layer force transmission device of the gas turbine is characterized by comprising a first component (1), a second component (2) and a third component (3), wherein the second component (2) comprises an upper part and a lower part, the upper part and the first component (1) form a Z-shaped structure, and the lower part and the third component (3) form a herringbone structure;
two sides of the Z-shaped structure are respectively provided with a baffle, the first component (1), the second component (2) and the baffles enclose an air guide cavity, correspondingly, the upper part is provided with an air guide hole (201) communicated with the air guide cavity, and the first component (1) is provided with an air outlet (101) communicated with the air guide cavity.
2. The double-deck force transfer device of a gas turbine according to claim 1, wherein the first member (1) comprises a horizontal plate (11) and a first inclined plate (12), wherein the air outlet (101) is located on the horizontal plate (11), and one end of the horizontal plate (11) is a free end, and the other end of the horizontal plate (11) is a connection end; the high end of the first inclined plate (12) is connected with the connecting end of the horizontal plate (11), and the low end of the first inclined plate (12) is gradually inclined towards the free end of the horizontal plate (11) and is connected with the upper part.
3. Gas turbine double-layer force transfer device according to claim 1, characterised in that the baffle comprises a first baffle (41) and a second baffle (42);
an inwards concave groove body is arranged on the first baffle plate (41), the upper end of the first baffle plate (41) is connected with the free end of the horizontal plate (11), and the lower end of the first baffle plate (41) is connected with the upper part;
the second baffle (42) is an inward concave arc plate, the upper end of the second baffle (42) is connected with the connecting end of the horizontal plate (11), and the lower end of the second baffle (42) is connected with the upper part.
4. The double-layer force transmission device of the gas turbine as claimed in claim 3, wherein the first baffle (41) comprises a first vertical plate (411), a first inclined plate (412), a second vertical plate (413), a second inclined plate (414) and a third vertical plate (415) which are connected in sequence from top to bottom, wherein the first vertical plate (411) is connected with the free end of the horizontal plate (11), the third vertical plate (415) is connected with the upper portion, and correspondingly, the concave groove body is composed of the first inclined plate (412), the second vertical plate (413) and the second inclined plate (414).
5. The double-layer force transmission device of the gas turbine as claimed in claim 1, wherein the second component (2) comprises a runner part (21) and a second inclined plate (22) which are sequentially connected from bottom to top, wherein the runner part (21) and the first component (1) form a Z-shaped structure, and the second inclined plate (22) and the third component (3) form a herringbone structure;
runner portion (21) and second swash plate (22) all incline to set up, and the lower extreme of second swash plate (22) is connected in the low side of runner portion (21), and the lower extreme of second swash plate (22) is to keeping away from runner portion (21) direction slope gradually.
6. The double-layer force transmission device of the gas turbine as claimed in claim 5, wherein a cavity adapted to a gas turbine runner is arranged in the runner portion (21), and the air guide holes (201) are located on the side wall of the cavity.
7. The double-deck power transmission device of a gas turbine according to any one of claims 5 to 6, wherein the third member (3) comprises a third inclined plate (31), the upper end of the third inclined plate (31) is connected with the high end of the runner part (21), and the lower end of the third inclined plate (31) is gradually inclined in the direction away from the runner part (21), so that the extension line of the third inclined plate (31) can intersect with the extension line of the second inclined plate (22) above the third inclined plate.
8. The gas turbine double-layer force transfer device according to claim 7, wherein the included angle between the second inclined plate (22) and the third inclined plate (31) is within 42.5-45.5 °;
the included angle between the second inclined plate (22) and the horizontal direction is 60 degrees +/-1 degrees, and the included angle between the third inclined plate (31) and the horizontal direction is 76 degrees +/-30 degrees.
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| CN202210123139.XA CN114151194B (en) | 2022-02-10 | 2022-02-10 | Double-layer force transmission device of gas turbine |
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| CN202210123139.XA CN114151194B (en) | 2022-02-10 | 2022-02-10 | Double-layer force transmission device of gas turbine |
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