CN116733613B - Transition section structure of gas turbine - Google Patents
Transition section structure of gas turbine Download PDFInfo
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- CN116733613B CN116733613B CN202311003395.6A CN202311003395A CN116733613B CN 116733613 B CN116733613 B CN 116733613B CN 202311003395 A CN202311003395 A CN 202311003395A CN 116733613 B CN116733613 B CN 116733613B
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- 230000007704 transition Effects 0.000 title claims abstract description 135
- 238000009792 diffusion process Methods 0.000 claims abstract description 15
- 230000000903 blocking effect Effects 0.000 claims abstract description 8
- 238000001816 cooling Methods 0.000 claims description 14
- 238000007789 sealing Methods 0.000 claims description 11
- 239000000919 ceramic Substances 0.000 claims description 5
- 239000000835 fiber Substances 0.000 claims description 5
- 210000001503 joint Anatomy 0.000 claims description 5
- 239000012774 insulation material Substances 0.000 claims description 4
- 238000000926 separation method Methods 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 21
- 230000000295 complement effect Effects 0.000 description 9
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 4
- 238000004378 air conditioning Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 229910052786 argon Inorganic materials 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 239000000956 alloy Substances 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
Classifications
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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
- F02C7/24—Heat or noise insulation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/005—Selecting particular materials
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
- F01D25/145—Thermally insulated casings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/26—Double casings; Measures against temperature strain in casings
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Materials Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention belongs to the technical field of gas turbines, and particularly relates to a transition section structure of a gas turbine, which comprises an outer casing ring assembly and an inner casing ring assembly; the transition section outer casing of the outer casing ring assembly is in a conical ring shape, and the outer flow passage bow-shaped piece is arranged on the inner ring side of the transition section outer casing; the outer heat shield is arranged between the transition section outer casing and the outer flow passage bow-shaped piece; the inner casing of the transition section of the inner casing ring assembly is conical ring-shaped, and the inner runner bow-shaped piece is arranged on the outer ring side of the outer casing of the transition section; the inner heat shield is arranged between the inner casing of the transition section and the arch piece of the inner runner and used for blocking and diffusing heat transferred from the transition channel to the inner casing of the transition section. After the heat separation is carried out on the inner heat shield and the outer heat shield in the scheme, the high temperature born by the transition section outer casing and the transition section inner casing can be effectively reduced, so that the influence of high temperature gas in the diffusion transition passage on the structural stability of the transition section outer casing and the transition section inner casing is reduced.
Description
Technical Field
The invention belongs to the technical field of gas turbines, and particularly relates to a transition section structure of a gas turbine.
Background
The transition section of the gas turbine is generally arranged between the gas generator and the power turbine, and a transition passage with an increased flow passage diameter is generally arranged in the transition section, and the transition passage has the function of carrying out speed reduction and diffusion on high-temperature high-pressure airflow of the gas turbine and then transmitting the high-temperature high-pressure airflow to the gas inlet of the power turbine.
With the development of technology, the requirements on the efficiency of the gas turbine are higher and higher, and the temperature of the output airflow at the rear end of the gas generator is higher and higher, so that the inlet temperature of the transition section is higher and higher. For low pressure turbine outlet temperatures having an average temperature of about 1000 ℃, transition structures fabricated from conventional superalloys tend to suffer from a series of problems in terms of thermal deformation and reduced surface quality during use.
Therefore, there is a need for a structure that reduces deformation of the transition section in high temperature gas streams.
Disclosure of Invention
In order to solve the problem that the transition section in the prior art deforms when bearing high temperature, the scheme provides a transition section structure of a gas turbine.
The technical scheme adopted by the invention is as follows:
a transition section structure of a gas turbine comprises an outer casing ring component and an inner casing ring component; the outer casing ring assembly is arranged on the radial outer side of the inner casing ring assembly, and a conical ring-shaped diffusion transition channel is formed between the outer casing ring assembly and the inner casing ring assembly;
the outer casing ring assembly comprises a transition section outer casing, an outer heat shield and an outer flow path bow; the transition section outer casing is in a conical ring shape, and the outer flow passage bow-shaped piece is arranged on the inner ring side of the transition section outer casing; the outer heat shield is arranged between the transition section outer casing and the outer flow passage bow-shaped piece and is used for blocking and diffusing heat transferred from the transition passage to the transition section outer casing;
the inner casing ring assembly comprises a transition section inner casing, an inner heat shield and an inner runner bow; the inner casing of the transition section is in a conical ring shape, and the inner runner bow-shaped piece is arranged on the outer ring side of the outer casing of the transition section; the inner heat shield is arranged between the inner casing of the transition section and the arch piece of the inner runner and used for blocking and diffusing heat transferred from the transition channel to the inner casing of the transition section.
As an alternative or complementary design to the above-described transition section structure: the outer flow passage bow-shaped piece and the inner flow passage bow-shaped piece respectively comprise a plurality of unit petals, adjacent unit petals are connected in a spliced mode through sealing sheets, and the sealing sheets are spliced with the unit petals.
As an alternative or complementary design to the above-described transition section structure: the inner heat shield and the outer heat shield respectively comprise a plurality of unit shields, and adjacent unit shields are connected through splicing.
As an alternative or complementary design to the above-described transition section structure: the channel between the outer runner bow and the transition section outer casing is divided into an outer screen outer channel and an outer screen inner channel by an outer heat shield; the front side edge of the outer heat shield is connected with the front section of the outer casing of the transition section, and the rear side edge of the outer heat shield is spaced from the rear section of the outer casing of the transition section; a plurality of outer air film holes are arranged on the side wall of the outer flow passage bow-shaped piece; the cold air fed into the outer screen outer channel is detoured into the outer screen inner channel at the rear section of the outer casing, and enters the diffusion transition channel through the outer air film hole so as to form an air film on the inner wall of the outer flow passage bow member.
As an alternative or complementary design to the above-described transition section structure: an outer cold air front hole and a front section rear groove are arranged at the front section of the outer casing; the front section rear groove is positioned at the rear part of the front section of the outer casing, the notch of the front section rear groove is communicated with the outer screen outer channel, and the outer cold air front hole is positioned at the front part of the front section of the outer casing and is communicated with the front section rear groove; when the front section of the outer casing is in butt joint with the low-pressure turbine casing, the rear air holes of the turbine casing at the rear part of the low-pressure turbine casing are opposite to the front outer air holes, so that the air conditioner sent out by the low-pressure turbine casing can enter the outer screen outer channel through the front outer air holes.
As an alternative or complementary design to the above-described transition section structure: the outer heat shield is fixed to the transition section outer casing through the front screw and the rear screw, a tension wire is connected between nuts of the two screws, and the tension wire abuts against the inner side of the outer heat shield so as to limit warping of the outer heat shield.
As an alternative or complementary design to the above-described transition section structure: the channel between the inner runner bow and the transition section inner casing is separated into an inner screen outer channel and an inner screen inner channel by an inner heat shield; the front side edge and the rear side edge of the inner heat shield are respectively connected with the front section of the inner casing and the rear section of the inner casing of the transition section; the cold air flow sent into the inner screen outer channel passes through the inner wall of the inner flow passage bow member, thereby realizing the cooling of the inner flow passage bow member.
As an alternative or complementary design to the above-described transition section structure: a plurality of front cold air ducts are arranged in the inner screen inner channel; the front end of the front cold air duct is connected with an inner cold air front hole of the front section of the inner casing, so that cold air in the low-pressure turbine casing can enter the front cold air duct when the front section of the inner casing is in butt joint with the low-pressure turbine casing; the rear end of the front cold air duct is connected with an inner cold air rear hole at the rear section of the inner casing, and the inner cold air rear hole is communicated to the outside of the rear section of the outer casing through the rear cold air duct.
As an alternative or complementary design to the above-described transition section structure: a hollow guide vane is arranged between the rear section of the inner casing and the rear section of the outer casing; the outer wall of the rear section of the outer casing is provided with a rear cooling air inlet hole, the rear side of the rear section of the casing is provided with an outer cooling air rear hole, and the rear side of the rear section of the inner casing is provided with a rear section casing rear hole; and part of cold air entering the inner side of the rear section of the outer casing is sent to the rear hole of the outer casing through the rear cold air inlet hole, and the other part of cold air entering the inner side of the rear section of the outer casing is sent to the rear hole of the rear section casing through the cavity of the guide vane through the rear cold air inlet hole, and the cold air at the rear hole of the outer casing and the rear hole of the rear section casing is used for conveying to the rear side part of the transition section structure.
As an alternative or complementary design to the above-described transition section structure: the inner heat shield and the outer heat shield are made of ceramic fiber heat insulation materials.
The beneficial effects of the invention are as follows:
in the structure of the scheme, the outer casing of the transition section and the inner casing of the transition section are used as supporting frameworks of the structure of the transition section, and after the inner heat shield and the outer heat shield are arranged for heat isolation, the high temperature born by the outer casing of the transition section and the inner casing of the transition section can be effectively reduced, so that the influence of high temperature gas in a diffusion transition passage on the structural stability of the outer casing of the transition section and the inner casing of the transition section is reduced; in addition, the inner heat shield and the outer heat shield are made of ceramic fiber heat-insulating materials, and the materials have the advantages of high temperature resistance, good heat stability, high compressive strength, long service life, low heat conductivity, mechanical vibration resistance, easiness in cutting and installation and the like, so that the cost is effectively saved and the heat-insulating effect is ensured; in the structure of the scheme, the outer heat shield is formed by the circuitous design of the outer shield outer channel and the outer shield inner channel, so that a double-layer cooling air barrier is formed, the cooling air can enter the diffusion transition channel through the outer air film hole while the cooling of the two sides of the outer heat shield can be ensured, and the outer runner bow-shaped piece can be protected; the interior heat screen department in the structure of this scheme, through the circuitous design that interior screen outer passageway and interior screen inner passageway formed, can effectually block the air conditioning in the preceding air conditioning pipe by the heating to guarantee the temperature of the air conditioning of the back side part of changeover portion.
Drawings
In order to more clearly illustrate the embodiments of the present solution or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below.
FIG. 1 is a partial cross-sectional view of a transition section structure of a gas turbine
FIG. 2 is a partial cross-sectional view of a transition section structure of a gas turbine;
FIG. 3 is a rear side view of the outer casing ring assembly;
FIG. 4 is a view showing the state of use of the sealing sheet;
FIG. 5 is a view of the use of the tensioning wire;
FIG. 6 is a state diagram of the turbine case aft air hole interfacing with the outer cold air forward hole;
fig. 7 is a mating structure diagram of the outer casing rear section, guide vanes, and inner casing rear section.
In the figure: 1-a transition section outer casing; 11-an outer casing front section; 111-outer cold air front hole; 112-front section rear groove; 12-the middle section of the outer casing; 13-the rear section of the outer casing; 131-outer cold air rear hole; 132-rear cold air inlet; 2-an outer heat shield; 21-an outer screen outer channel; 22-an outer screen inner channel; 3-outer flow path bows; 31-screws; 32-sealing sheets; 33-tensioning the wire; 4-a transition section inner casing; 41-an inner casing front section; 411-low pressure turbine seal ring; 412-a second seal ring; 413-inner cold air front hole; 42-the middle section of the inner casing; 43-rear section of inner casing; 431-a power turbine seal ring; 432-inner cold air rear hole; 433-rear section casing rear hole; 5-an inner heat shield; 51-an inner-screen outer channel; 6-an inner runner bow; 7-a front cold air duct; 8-guide vanes; 9-a post-cool air duct; 10-low pressure turbine casing; 101-turbine casing aft air holes.
Detailed Description
The technical solutions of the present embodiment will be clearly and completely described below with reference to the accompanying drawings, and the described embodiments are only some embodiments, but not all embodiments, and all other embodiments obtained by those skilled in the art without making any creative effort based on the embodiments of the present embodiment are all within the protection scope of the present solution.
Example 1
As shown in fig. 1 to 7, the present embodiment designs a transition section structure of a gas turbine, including an outer casing ring assembly and an inner casing ring assembly; the outer casing ring assembly is in a conical ring shape and is arranged on the radial outer side of the inner casing ring assembly, a diffusion transition channel is formed between the outer casing ring assembly and the inner casing ring assembly, and the diffusion transition channel is in a conical ring shape and is used for decelerating and diffusing high-temperature high-pressure air flow discharged by the combustion chamber of the gas turbine and then transmitting the high-temperature high-pressure air flow to the air inlet of the power turbine so as to drive the power turbine to rotate.
The outer casing ring assembly comprises a transition section outer casing 1, an outer heat shield 2, an outer flow path bow 3 and the like; the transition section outer casing 1 is in a conical ring shape and comprises an outer casing front section 11, an outer casing middle section 12 and an outer casing rear section 13 which are sequentially arranged from front to back, and two ends of the outer casing middle section 12 are respectively connected with the outer casing front section 11 and the outer casing rear section 13 in an argon arc welding connection mode. The outer flow passage bow member 3 is arranged on the inner ring side of the transition section outer casing 1, the wall surface of the outer flow passage bow member 3 is separated from the transition section outer casing 1 by a certain distance, hooks are arranged on the outer side of the front part of the outer flow passage bow member 3, and grooves matched with the hooks are arranged on the inner ring side of the outer casing front section 11. The outer heat shield 2 is arranged between the transition section outer casing 1 and the outer flow passage bow-shaped piece 3 and is used for blocking heat transferred from the diffusion transition passage to the transition section outer casing 1; the outer heat shield 2 is made of ceramic fiber heat insulation material.
The inner casing ring assembly comprises a transition section inner casing 4, an inner heat shield 5, an inner runner bow 6 and the like; the transition section inner casing 4 is cone-shaped and comprises an inner casing front section 41, an inner casing middle section 42 and an inner casing rear section 43 which are sequentially arranged from front to back, and two ends of the inner casing middle section 42 are respectively connected with the inner casing front section 41 and the inner casing rear section 43 in an argon arc welding connection mode. The inner runner bow 6 is arranged on the outer ring side of the outer casing 1 of the transition section, annular protrusions are arranged on the front side and the rear side of the inner runner bow 6, and annular grooves matched with the annular protrusions are arranged on the inner ring side of the inner casing front section 41 and the guide blades 8 at the inner casing rear section 43. The inner heat shield 5 is arranged between the transition section inner casing 4 and the inner runner bow-shaped piece 6 and is used for blocking and diffusing heat transferred from the transition channel to the transition section inner casing 4, and the inner heat shield 5 is made of ceramic fiber heat insulation materials.
In the above structure, after heat blocking is carried out through setting up interior heat screen 5 and outer heat screen 2, can effectually reduce the high temperature that the outer receiver 1 of changeover portion and the interior receiver 4 of changeover portion bore to reduce the influence of the high temperature gas in the diffusion transition passageway to the outer receiver 1 of changeover portion and the interior receiver 4 structural stability of changeover portion. Under the working environment of high-temperature and high-pressure fuel gas, the temperature of the inner casing 4 of the transition section and the temperature of the outer casing 1 of the transition section are greatly reduced, and the problem of deformation of the inner casing and the outer casing made of high-temperature alloy materials is solved to a certain extent.
In addition, the mode of hook connection between the outer runner bow member 3 and the outer casing front section 11 and the mode of clamping connection between the inner runner bow member 6 and the inner casing front section 41 can be used for effectively avoiding the perforation, meanwhile, the outer casing 1 and the outer runner bow member 3 of the transition section can form a double-layer wall structure, the strength and the rigidity of the transition section are both beneficial, the fasteners are omitted, the disassembly and the assembly are more convenient, and the weight is reduced.
In addition, in order to further facilitate the disassembly and assembly of the outer runner bow 3, the outer runner bow 3 and the inner runner bow 6 respectively comprise a plurality of unit petals, the unit petals are fan-shaped and fan-shaped, adjacent unit petals are spliced and connected through a sealing piece 32, the sealing piece 32 is spliced with the unit petals, and specifically: the sealing piece 32 is arranged along the airflow direction of the diffusion transition channel, and slots are formed in the edges of two sides of the unit valve, so that the sealing piece 32 can be inserted into the corresponding slots.
In order to facilitate the installation of the inner heat shield 5 and the outer heat shield 2, the installation of the inner heat shield 5 and the outer heat shield 2 also respectively comprises a plurality of unit shields, and the adjacent unit shields are connected through splicing. The left and right sides of each unit screen of the outer heat shield 2 are fixed to the outer casing middle section 12 by a front screw 31 and a rear screw 31, holes for threading a tightening wire 33 are formed in nuts of the front screw 31 and the rear screw 31, and the tightening wire 33 is connected between nuts of the front screw 31 and the rear screw 31 and is tightened after being twisted, so that the tightening wire 33 can abut against the inner side of the outer heat shield 2 to limit warping of the outer heat shield 2.
Example 2
On the basis of the structure of embodiment 1, the structure in this embodiment is designed for cooling the transition structure of the gas turbine by cool air.
For cold air cooling of the outer casing ring assembly, a channel is formed between the outer channel bow 3 and the transition piece outer casing 1 at a distance and is separated by the outer heat shield 2 into an outer shield outer channel 21 and an outer shield inner channel 22, the outer shield outer channel 21 being located between the outer heat shield 2 and the transition piece outer casing 1 and the outer shield inner channel 22 being located between the outer heat shield 2 and the outer channel bow 3; the front side edge of the outer heat shield 2 is connected with the front section 11 of the outer casing of the transition section outer casing 1, so that air entering from the front end of the outer casing outer channel 21 is prevented from directly leaking into the outer casing inner channel 22, a gap is reserved between the rear side edge of the outer heat shield 2 and the rear section 13 of the outer casing of the transition section outer casing 1, and therefore cold air of the outer casing outer channel 21 can be returned into the outer casing inner channel 22 from the gap, and a plurality of outer air film holes are formed in the side wall of the outer flow channel bow 3; the cold air in the outer screen inner channel 22 can enter the diffusion transition channel through the outer air film holes to form an air film on the inner wall of the outer flow path bow 3. Through the circuitous design that outer screen outer passageway 21 and outer screen inner passageway 22 formed, form double-deck cooling air barrier, can guarantee the two sides cooling of outer heat screen 2, the cold air also enters into the diffusion transition passageway through outer air film hole simultaneously in, protects outer runner bow-shaped piece 3.
An outer cold air front hole 111 and a front section rear groove 112 are arranged on the outer casing front section 11; the front section rear groove 112 is positioned at the rear part of the outer casing front section 11; the notch of the front section rear groove 112 is inclined to the front end of the outer screen outer passage 21 and communicates with the outer screen outer passage 21, and the outer cold air front hole 111 is located in the front of the outer casing front section 11 and communicates with the front section rear groove 112. When the outer casing front section 11 is abutted against the low pressure turbine casing 10, the turbine casing rear air hole 101 on the rear outer side of the low pressure turbine casing 10 is opposite to the outer cold air front hole 111, so that cold air sent out by the low pressure turbine casing 10 can enter the outer screen outer passage 21 through the outer cold air front hole 111.
For cold air cooling of the inner casing ring assembly, the channel between the inner flowpath segment 6 and the transition section inner casing 4 is separated by an inner heat shield 5 and forms an inner outer screen channel 51 and an inner screen inner channel, respectively, the inner outer screen channel 51 being located outside the inner heat shield 5 and the inner screen inner channel being located inside the inner heat shield 5; the front side edge and the rear side edge of the inner heat screen 5 are respectively connected with the front section 41 and the rear section 43 of the inner casing 4 of the transition section, so that the cold air in the inner screen outer channel 51 is reduced from entering the inner screen inner channel; an inner cold air front hole 413 and an air inlet hole of an inner screen outer channel 51 are arranged on the front side of the transition section inner casing 4; when the inner casing front section 41 is in butt joint with the low-pressure turbine casing 10, cold air is sent into the inner screen outer channel 51 through the air inlet hole of the inner screen outer channel 51, and flows through the inner wall of the inner runner arch piece 6, so that cooling of the inner runner arch piece 6 is achieved, the guide blades 8 are arranged at the inner casing rear section 43, the rear side edges of the inner heat shields 5 are connected with the inner blade edges of the guide blades 8, gaps are formed between the guide blades 8 and the inner casing rear section 43, and cold air in the inner screen outer channel 51 can enter the guide blades 8 from the gaps.
A plurality of front cold air ducts 7 are arranged in the inner screen inner channel; the front end of the front cold air duct 7 is connected with an inner cold air front hole 413 of the inner casing front section 41, so that cold air in the low-pressure turbine casing 10 can enter the front cold air duct 7 when the inner casing front section 41 is in butt joint with the low-pressure turbine casing 10; the rear end of the front cold air duct 7 is connected with an inner cold air rear hole 432 of the inner casing rear section 43, the inner cold air rear hole 432 is communicated with the rear cold air duct 9, the rear cold air duct 9 passes through the guide vane 8 and extends out of the outer casing rear section 13, and the front cold air duct 7 and the rear cold air duct 9 can convey cold air to the outside of the outer casing rear section 13, so that cold air is provided for a part of the gas turbine which needs to be cooled.
In addition, in order to lead out the cool air at the compressor to the transition section structure and realize the cooling of the rear side part of the transition section structure: a hollow guide vane 8 is arranged between the inner casing rear section 43 and the outer casing rear section 13; a rear cold air inlet hole 132 is provided on the outer wall of the outer casing rear section 13, an outer cold air rear hole 131 is provided at the rear side of the casing rear section, and a rear casing rear hole 433 is provided at the rear side of the inner casing rear section 43. The cold air sent out by the air compressor enters the annular cavity between the outer blade edge of the guide blade 8 and the rear section 13 of the outer casing through the rear cold air inlet 132, then a part of the cold air is sent to the rear hole 131 of the outer cold air and then is sent to the rear side part of the transition section structure through the rear hole 131 of the outer cold air, and the other part of the cold air in the annular cavity is sent to the annular cavity between the outer blade edge and the rear section 43 of the inner casing through the hollow cavity in the guide blade 8 and then is sent to the rear hole 433 of the rear casing and is sent to the rear side part of the transition section structure through the rear hole 433 of the rear casing.
Further, a low-pressure turbine seal ring 411 and a second seal ring 412 are provided on the front side of the inner case front section 41, and a power turbine seal ring 431 is provided on the rear side of the inner case rear section 43. The low pressure turbine seal ring 411, the second seal ring 412, and the power turbine seal ring 431 are all used for sealing of gas turbine components.
The above examples are presented for the purpose of illustration only and are not intended to be limiting of the embodiments; it is not necessary here nor is it exhaustive of all embodiments. And obvious variations or modifications thereof are contemplated as falling within the scope of the present technology.
Claims (9)
1. A gas turbine's changeover portion structure, characterized in that: comprises an outer casing ring component and an inner casing ring component; the outer casing ring assembly is arranged on the radial outer side of the inner casing ring assembly, and a conical ring-shaped diffusion transition channel is formed between the outer casing ring assembly and the inner casing ring assembly;
the outer casing ring assembly comprises a transition section outer casing (1), an outer heat shield (2) and an outer flow path bow (3); the transition section outer casing (1) is in a conical ring shape, and the outer flow passage bow-shaped piece (3) is arranged on the inner ring side of the transition section outer casing (1); the outer heat shield (2) is arranged between the transition section outer casing (1) and the outer flow passage bow-shaped piece (3) and is used for blocking and diffusing heat transferred from the transition passage to the transition section outer casing (1);
the inner casing ring assembly comprises a transition section inner casing (4), an inner heat shield (5) and an inner runner bow (6); the inner casing (4) of the transition section is in a conical ring shape, and the inner runner arch piece (6) is arranged on the outer ring side of the outer casing (1) of the transition section; the inner heat shield (5) is arranged between the transition section inner casing (4) and the inner runner bow-shaped piece (6) and is used for blocking and diffusing heat transferred from the transition channel to the transition section inner casing (4);
the channel between the outer runner bow-shaped piece (3) and the transition section outer casing (1) is divided into an outer screen outer channel (21) and an outer screen inner channel (22) by an outer heat shield (2); the front side edge of the outer heat screen (2) is connected with the front section (11) of the outer casing of the transition section outer casing (1), and the rear side edge of the outer heat screen is spaced from the rear section (13) of the outer casing of the transition section outer casing (1); a plurality of outer air film holes are arranged on the side wall of the outer flow passage bow-shaped piece (3); the cold air fed into the outer screen outer channel (21) bypasses to the inner screen inner channel (22) at the rear section (13) of the outer casing, and enters the diffusion transition channel through the outer air film hole so as to form an air film on the inner wall of the outer flow passage bow member (3).
2. The gas turbine transition section structure of claim 1, wherein: the outer flow passage bow-shaped piece (3) and the inner flow passage bow-shaped piece (6) respectively comprise a plurality of unit petals, adjacent unit petals are spliced and connected through a sealing piece (32), and the sealing piece (32) is spliced with the unit petals.
3. The gas turbine transition section structure of claim 1, wherein: the inner heat shield (5) and the outer heat shield (2) respectively comprise a plurality of unit shields, and adjacent unit shields are connected through splicing.
4. The gas turbine transition section structure of claim 1, wherein: an outer cold air front hole (111) and a front section rear groove (112) are arranged on the outer casing front section (11); the front section rear groove (112) is positioned at the rear part of the front section (11) of the outer casing, the notch of the front section rear groove (112) is communicated with the outer screen outer channel (21), and the outer cold air front hole (111) is positioned at the front part of the front section (11) of the outer casing and is communicated with the front section rear groove (112); when the outer casing front section (11) is abutted against the low-pressure turbine casing (10), a turbine casing rear air hole (101) at the rear part of the low-pressure turbine casing (10) is opposite to the outer cold air front hole (111), so that cold air sent out by the low-pressure turbine casing (10) can enter the outer screen outer channel (21) through the outer cold air front hole (111).
5. The gas turbine transition section structure of claim 1, wherein: the outer heat shield (2) is fixed to the transition section outer casing (1) through a front screw (31) and a rear screw (31), a tensioning wire (33) is connected between nuts of the two screws (31), and the tensioning wire (33) abuts against the inner side of the outer heat shield (2) so as to limit warping of the outer heat shield (2).
6. The gas turbine transition section structure according to claim 4 or 5, characterized in that: the channel between the inner runner bow-shaped piece (6) and the transition section inner casing (4) is divided into an inner screen outer channel (51) and an inner screen inner channel by an inner heat shield (5); the front side edge and the rear side edge of the inner heat shield (5) are respectively connected with the front section (41) and the rear section (43) of the inner casing (4) of the transition section; the cold air flow sent into the inner screen outer channel (51) passes through the inner wall of the inner flow passage bow-shaped piece (6), thereby realizing the cooling of the inner flow passage bow-shaped piece (6).
7. The gas turbine transition section structure of claim 6, wherein: a plurality of front cold air ducts (7) are arranged in the inner screen inner channel; the front end of the front cold air duct (7) is connected with an inner cold air front hole (413) of the inner casing front section (41), so that cold air in the low-pressure turbine casing (10) can enter the front cold air duct (7) when the inner casing front section (41) is in butt joint with the low-pressure turbine casing (10); the rear end of the front cold air duct (7) is connected with an inner cold air rear hole (432) of the inner casing rear section (43), and the inner cold air rear hole (432) is communicated to the outside of the outer casing rear section (13) through the rear cold air duct (9).
8. The gas turbine transition section structure of claim 7, wherein: a hollow guide vane (8) is arranged between the inner casing rear section (43) and the outer casing rear section (13); a rear cold air inlet hole (132) is formed in the outer wall of the outer casing rear section (13), an outer cold air rear hole (131) is formed in the rear side of the casing rear section, and a rear casing rear hole (433) is formed in the rear side of the inner casing rear section (43); part of the cold air entering the inner side of the outer casing rear section (13) is sent to the outer cold air rear hole (131) through the rear cold air inlet hole (132), and the other part of the cold air entering the inner side of the outer casing rear section (13) is sent to the rear casing rear hole (433) through the cavity of the guide vane (8) through the rear cold air inlet hole (132), and the cold air at the rear casing rear hole (433) and the outer cold air rear hole (131) is used for conveying to the rear side part of the transition section structure.
9. A gas turbine transition section structure according to any one of claims 1 to 3, wherein: the inner heat shield (5) and the outer heat shield (2) are made of ceramic fiber heat insulation materials.
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| CN202311003395.6A CN116733613B (en) | 2023-08-10 | 2023-08-10 | Transition section structure of gas turbine |
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| CN117569923B (en) * | 2024-01-12 | 2024-04-05 | 成都中科翼能科技有限公司 | Turbine fulcrum structure of gas turbine |
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