CN118088792B - Bleed air assembly of double-layer runner casing of gas turbine - Google Patents
Bleed air assembly of double-layer runner casing of gas turbine Download PDFInfo
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- CN118088792B CN118088792B CN202410479836.8A CN202410479836A CN118088792B CN 118088792 B CN118088792 B CN 118088792B CN 202410479836 A CN202410479836 A CN 202410479836A CN 118088792 B CN118088792 B CN 118088792B
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- runner
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- 238000007789 sealing Methods 0.000 claims abstract description 36
- 238000007667 floating Methods 0.000 claims abstract description 25
- 239000007789 gas Substances 0.000 description 34
- 238000010586 diagram Methods 0.000 description 5
- 238000002485 combustion reaction Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 3
- 239000000446 fuel Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 239000011324 bead Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 239000000112 cooling gas Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
- 210000003437 trachea Anatomy 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N1/00—Sampling; Preparing specimens for investigation
- G01N1/02—Devices for withdrawing samples
- G01N1/22—Devices for withdrawing samples in the gaseous state
- G01N1/2226—Sampling from a closed space, e.g. food package, head space
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L41/00—Branching pipes; Joining pipes to walls
- F16L41/08—Joining pipes to walls or pipes, the joined pipe axis being perpendicular to the plane of a wall or to the axis of another pipe
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L5/00—Devices for use where pipes, cables or protective tubing pass through walls or partitions
- F16L5/02—Sealing
- F16L5/10—Sealing by using sealing rings or sleeves only
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N1/00—Sampling; Preparing specimens for investigation
- G01N1/02—Devices for withdrawing samples
- G01N1/22—Devices for withdrawing samples in the gaseous state
- G01N1/2226—Sampling from a closed space, e.g. food package, head space
- G01N2001/2238—Sampling from a closed space, e.g. food package, head space the gas being compressed or pressurized
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Biomedical Technology (AREA)
- Molecular Biology (AREA)
- Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- General Physics & Mathematics (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention belongs to the technical field of gas turbines, and particularly relates to an air entraining assembly of a double-layer runner casing of a gas turbine, which comprises an air entraining pipe and an air pipe guide cylinder; the air pipe guide cylinder is arranged between the outer-layer casing and the inner-layer casing; the inner part of the air entraining pipe is provided with an air entraining channel, the side wall of the inner end of the air entraining pipe is provided with an air entraining hole, and the air entraining hole is communicated with the air entraining pipe; when the air guide pipe is used, the inner end of the air guide pipe penetrates through the air guide pipe and extends into the inner layer runner, the outer end of the air guide pipe is arranged outside the outer casing, the air guide pipe is connected with the air guide pipe or the outer casing in a sealing mode, and the air inlet hole faces the air flow in the inner layer runner and guides the air flow in the inner layer runner out of the outer casing through the air guide channel. The sealing combination mode of the air pipe guide cylinder and the double-layer runner casing obviously improves the sealing performance; the floating sealing ring structure can compensate the movement of the outer end of the air pipe guide cylinder relative to the outer-layer casing through the floating sealing ring, so that the problem of dislocation of mounting holes caused by uncoordinated thermal deformation of the two-layer casing is avoided.
Description
Technical Field
The invention belongs to the technical field of gas turbines, and particularly relates to an air entraining assembly of a double-layer runner casing of a gas turbine.
Background
The gas turbine is known as a 'bright bead on crown' in the manufacturing industry, and is key core equipment for cleaning power generation and power devices. The working principle of the gas turbine is as follows: the gas compressed by the gas compressor enters the combustion chamber to be fully mixed with fuel, and then is changed into high-temperature high-pressure gas after being combusted, and the turbine is blown to do work to convert heat energy into mechanical energy.
When the gas turbine is in a use state, the state of the high-temperature and high-pressure gas after combustion often needs to be detected, including parameters such as temperature, pressure and the like. If the high-temperature and high-pressure gas state after combustion is to be obtained, an air entraining pipe is often required to be installed through a double-layer runner casing for sampling, and then data are obtained through an analyzer.
At present, a method for collecting high-temperature and high-pressure gas of a gas turbine is to open holes on a double-layer runner casing of the gas turbine, weld an installation seat on an outer-layer casing, and then fix a bleed pipe on the installation seat of the outer-layer casing through the double-layer runner, so that the burnt high-temperature and high-pressure gas is led out.
The above structure is used for leading out the gas in the flow channel, and has many defects such as: the double-layer casing is provided with holes, the concentricity requirements of the inner hole and the outer hole are higher, so that the smooth passing of the gas-guiding pipe is ensured, and the processing difficulty is higher; secondly, the existing bleed air pipe has poor tightness when passing through the double-layer runner casing, and air flow in the inner-layer runner easily enters the outer-layer runner along a gap between the inner-layer casing and the bleed air pipe, so that the air loss and measurement error of the inner-layer runner are caused; finally, because the gas temperature difference of the inner and outer runners is large, the thermal deformation of the inner and outer cases is inconsistent, deformation dislocation of the mounting holes is easy to cause, subsequent disassembly and assembly are difficult, even extrusion is caused, damage is caused to the air-entraining pipe, and meanwhile the structural stability of the gas turbine is affected.
Disclosure of Invention
In order to solve the problem of sealing between the gas-guiding pipe and the double-layer runner casing in the prior art, the scheme provides a gas-guiding component of the double-layer runner casing of the gas turbine.
The technical scheme adopted by the invention is as follows:
The air entraining assembly of the double-layer runner casing of the gas turbine comprises an air entraining pipe and an air pipe guide cylinder;
The double-layer runner casing comprises an inner-layer casing and an outer-layer casing, the outer-layer casing is coaxially sleeved outside the inner-layer casing, an inner-layer runner is arranged in the inner-layer casing, and an outer-layer runner is arranged between the outer-layer casing and the inner-layer casing;
The air duct guide tube is in a tube shape, and is arranged between the outer-layer casing and the inner-layer casing when in use, the inner end of the air duct guide tube is in sealing connection with the inner-layer casing, and the outer end of the air duct guide tube is in sealing connection with the outer-layer casing;
The inner part of the air entraining pipe is provided with an air entraining channel, the side wall of the inner end of the air entraining pipe is provided with an air entraining hole, and the air entraining hole is communicated with the air entraining pipe; when the air guide pipe is used, the inner end of the air guide pipe penetrates through the air guide pipe and extends into the inner layer runner, the outer end of the air guide pipe is arranged outside the outer casing, the air guide pipe is connected with the air guide pipe or the outer casing in a sealing mode, and the air inlet hole faces the air flow in the inner layer runner and guides the air flow in the inner layer runner out of the outer casing through the air guide channel.
Alternatively or in addition to the bleed air assembly of the double runner casing of the gas turbine as described above: an inner mounting hole is formed in the side wall of the inner-layer casing, and the inner end of the air pipe guide cylinder is connected to the inner mounting hole in a sealing mode.
Alternatively or in addition to the bleed air assembly of the double runner casing of the gas turbine as described above: the inner mounting hole is an inner threaded hole, and the inner end of the tracheal catheter is provided with an external threaded part which is in threaded fit with the inner threaded hole.
Alternatively or in addition to the bleed air assembly of the double runner casing of the gas turbine as described above: a second convex ring part is arranged at the inner end of the tracheal catheter; when the external thread part is screwed on the inner mounting hole, the second convex ring part abuts against the outer wall surface of the inner-layer casing.
Alternatively or in addition to the bleed air assembly of the double runner casing of the gas turbine as described above: an outer mounting hole is formed in the side wall of the outer casing, and a mounting ring seat is welded on the outer casing at the outer mounting hole; the outer side wall of the outer end of the tracheal catheter is provided with a ring groove, a floating sealing ring is arranged at the ring groove, and the outer side wall of the floating sealing ring is in sealing contact with the inner wall of the mounting ring seat.
Alternatively or in addition to the bleed air assembly of the double runner casing of the gas turbine as described above: the outer annular wall of the floating sealing ring is a convex curved surface; the convex curved surface is a part of a spherical surface.
Alternatively or in addition to the bleed air assembly of the double runner casing of the gas turbine as described above: the floating sealing ring is formed by splicing a left half ring and a right half ring; the two ends of the left semi-ring and the right semi-ring are respectively provided with a step surface and are mutually meshed.
Alternatively or in addition to the bleed air assembly of the double runner casing of the gas turbine as described above: the air guide pipe is provided with a flange part, and the flange part can be fixed on the mounting ring seat through screws.
Alternatively or in addition to the bleed air assembly of the double runner casing of the gas turbine as described above: the outer end of the tracheal catheter is provided with an inner hexagonal hole.
Alternatively or in addition to the bleed air assembly of the double runner casing of the gas turbine as described above: a locking gasket is arranged between the flange part and the mounting ring seat; the locking gasket comprises an annular main body, an L-shaped lock tongue is arranged on the inner side of the annular main body, and the L-shaped lock tongue can be in snap fit with the wall of the inner hexagonal hole.
The beneficial effects of the invention are as follows:
1. The scheme optimizes and improves the structural form on the basis of opening the double-layer runner casing, increases the air duct guide cylinder, and remarkably improves the tightness in a sealing combination mode of the air duct guide cylinder and the double-layer runner casing;
2. In addition, when this scheme set up the floating seal ring structure, still can compensate the removal of trachea guide tube outer end for the outer shell casing through the floating seal ring, avoided the problem that the mounting hole misplaced that two-layer casing leads to because of thermal deformation is inconsistent.
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 an exploded view of the bleed air assembly as assembled;
FIG. 2 is a state diagram of the bleed air assembly as assembled;
FIG. 3 is a block diagram of an air bleed tube;
FIG. 4 is a block diagram of a tracheal tube;
FIG. 5 is a block diagram of a floating seal ring;
Fig. 6 is a block diagram of the locking washer.
In the figure: 1-an air introducing pipe; 11-flange part; 12-bleed air channel; 13-windward holes; 2-locking gaskets; 21-an annular body; 22-a nail penetrating hole; 23-L-shaped lock tongue; 3-screws; 4-an airway tube; 41-an inner hexagonal hole; 42-a guide cap; 43-ring groove; 44-a first collar portion; 45-a second collar portion; 46-an external threaded portion; 5-floating seal rings; 51-left half ring; 52-right half ring; 53-convex curved surface; 54-step surface; 6-mounting a ring seat; 7-an outer-layer casing; 8-an inner-layer casing; 9-inner layer flow channels; 10-outer layer runner.
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 6, the present embodiment designs an air entraining assembly of a double-runner casing of a gas turbine, which comprises an air entraining pipe 1, an air pipe guide cylinder 4, a locking gasket 2, a floating sealing ring 5 and other components.
The double-layer runner casing of the gas turbine comprises an inner-layer casing 8 and an outer-layer casing 7, the outer-layer casing 7 is coaxially sleeved outside the inner-layer casing 8, an inner-layer runner 9 is arranged in the inner-layer casing 8, and an outer-layer runner 10 is arranged between the outer-layer casing 7 and the inner-layer casing 8; the gas flowing in the inner-layer runner 9 is high-temperature and high-pressure gas after fuel combustion, and the gas flowing in the outer-layer runner 10 is cooling gas for cooling the inner-layer casing 8.
The air duct guide tube 4 is in a tube shape, the air duct guide tube 4 is arranged between the outer-layer casing 7 and the inner-layer casing 8 when in use, the inner end of the air duct guide tube 4 is in sealing connection with the inner-layer casing 8, and the outer end is in sealing connection with the outer-layer casing 7. An inner mounting hole is arranged on the side wall of the inner-layer casing 8, and the inner end of the air pipe guide tube 4 is connected with the inner mounting hole in a sealing way. The air tube guide tube 4 is in sealing connection with the inner-layer casing 8 in various ways, such as: the inner mounting hole is an inner threaded hole, and the inner end of the tracheal catheter 4 is provided with an outer threaded part 46, and the outer threaded part 46 is in threaded fit with the inner threaded hole. The air pipe guide cylinder 4 and the inner-layer casing 8 are in threaded connection, so that the strength is high, the manufacturability is good, the processing difficulty of the air pipe guide cylinder 4 is small, the concentricity is high, and the cost can be effectively reduced.
The inside of the air entraining pipe 1 is provided with an air entraining channel 12, the side wall of the inner end of the air entraining pipe 1 is provided with an air welting hole 13, and the air welting hole 13 is communicated with the air entraining pipe 1; when the air-entraining device is used, the inner end of the air-entraining pipe 1 passes through the air pipe guide cylinder 4 and stretches into the inner layer runner 9, the outer end of the air-entraining pipe is arranged outside the outer casing 7, the air-entraining pipe 1 is in sealing connection with the air pipe guide cylinder 4 or the outer casing, and the air-entraining hole 13 faces the air flow in the inner layer runner 9 and guides the air flow in the inner layer runner 9 out of the outer casing through the air-entraining channel 12.
A second convex ring part 45 is arranged at the inner end of the tracheal catheter 4; when the external thread portion 46 is screwed to the inner mounting hole, the second collar portion 45 abuts against the outer wall surface of the inner casing 8.
An outer mounting hole is formed in the side wall of the outer casing 7, a mounting ring seat 6 is welded on the outer casing at the outer mounting hole, an annular groove 43 is formed in the outer side wall of the outer end of the tracheal catheter 4, a floating sealing ring 5 is mounted at the annular groove 43, and the outer annular wall of the floating sealing ring 5 is in sealing contact with the inner wall of the mounting ring seat 6. When the outer casing 7 moves radially outwards or radially inwards relative to the inner casing 8 (i.e. when the outer casing 7 and the inner casing 8 are close to each other or far away from each other), the floating seal ring 5 can slide in the axial direction of the mounting ring seat 6 and always remain sealed.
A guide tube cap 42 and a first convex ring part 44 are arranged at the outer end of the tracheal guide tube 4, and the annular groove 43 is formed between the guide tube cap 42 and the first convex ring part 44.
The outer annular wall of the floating seal ring 5 is a convex curved surface 53; the convex curved surface 53 is a part of a spherical surface; the convex curved surface 53 is configured such that the floating seal ring 5 can rotate in the mounting ring seat 6 and always remain sealed when the outer casing 7 moves axially forward or axially backward relative to the inner casing 8.
Through the structural design of the floating seal ring 5, the air entraining assembly in the embodiment can perform space compensation when the inner-layer casing 8 and the outer-layer casing 7 move in different directions, and the problem of dislocation of mounting holes caused by uncoordinated thermal deformation of the casings is avoided. The characteristics of the spherical surface enable the outer-layer casing 7 and the inner-layer casing 8 to relatively move in any direction, and the spherical surface is always attached to the inner wall surface of the mounting ring seat 6, so that floating sealing is realized, and the characteristics of up-down, left-right movement of the spherical surface can well compensate transverse and longitudinal displacement deformation.
The floating sealing ring 5 is formed by splicing a left half ring 51 and a right half ring 52; the left half ring 51 and the right half ring 52 have stepped surfaces 54 at both ends thereof and are engaged with each other. The floating seal ring 5 adopts the design of splicing structure, so that the floating seal ring 5 can be conveniently installed at the outer end of the tracheal catheter 4.
The bleed air pipe 1 is provided with a flange portion 11, which flange portion 11 can be fastened to the mounting ring seat 6 by means of screws 3.
The outer end of the air pipe guide cylinder 4 is provided with an inner hexagonal hole 41, and when the air pipe guide cylinder 4 is in threaded connection with the inner-layer casing 8, the inner hexagonal hole 41 can be connected with a hexagonal wrench, so that screwing and mounting of the air pipe guide cylinder 4 are facilitated.
A locking gasket 2 is arranged between the flange part 11 and the mounting ring seat 6; the locking gasket 2 comprises an annular main body 21, an L-shaped lock tongue 23 is arranged on the inner side of the annular main body 21, the L-shaped lock tongue 23 can be in meshed fit with the hole wall of the inner hexagonal hole 41, one part of the L-shaped lock tongue 23 is attached to the end face of the tracheal catheter 4, and the other part of the L-shaped lock tongue 23 is attached to the hole wall of the inner hexagonal hole 41, so that the limit of the tracheal catheter 4 is realized. A plurality of through-nail holes 22 are annularly distributed on the annular main body 21, and the through-nail holes 22 are used for passing the bolts 3.
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 (7)
1. The utility model provides a gas-entraining subassembly of gas turbine double-deck runner receiver which characterized in that: comprises an air guiding pipe (1) and an air guiding pipe cylinder (4);
The double-layer runner casing comprises an inner-layer casing (8) and an outer-layer casing (7), the outer-layer casing (7) is coaxially sleeved outside the inner-layer casing (8), an inner-layer runner (9) is arranged in the inner-layer casing (8), and an outer-layer runner (10) is arranged between the outer-layer casing (7) and the inner-layer casing (8);
The air pipe guide cylinder (4) is in a tubular shape, the air pipe guide cylinder (4) is arranged between the outer-layer casing (7) and the inner-layer casing (8) when in use, the inner end of the air pipe guide cylinder (4) is in sealing connection with the inner-layer casing (8), and the outer end is in sealing connection with the outer-layer casing (7);
The inner part of the air entraining pipe (1) is provided with an air entraining channel (12), the side wall of the inner end of the air entraining pipe (1) is provided with an air welting hole (13), and the air welting hole (13) is communicated with the air entraining pipe (1); when the air-entraining device is used, the inner end of the air-entraining pipe (1) passes through the air pipe guide cylinder (4) and stretches into the inner layer runner (9), the outer end of the air-entraining pipe is arranged outside the outer casing (7), the air-entraining pipe (1) is in sealing connection with the air pipe guide cylinder (4) or the outer casing, and the air-entraining hole (13) is faced to the air flow of the inner layer runner (9) and guides the air flow of the inner layer runner (9) out of the outer casing through the air-entraining channel (12);
an inner mounting hole is formed in the side wall of the inner-layer casing (8), and the inner end of the air pipe guide cylinder (4) is connected to the inner mounting hole in a sealing manner;
an outer mounting hole is formed in the side wall of the outer casing (7), and a mounting ring seat (6) is welded on the outer casing at the outer mounting hole; a ring groove (43) is formed in the outer side wall of the outer end of the tracheal catheter (4), a floating sealing ring (5) is arranged at the ring groove (43), and the outer ring wall of the floating sealing ring (5) is in sealing contact with the inner wall of the mounting ring seat (6);
The outer annular wall of the floating sealing ring (5) is a convex curved surface (53); the convex curved surface (53) is a part of a spherical surface.
2. The gas turbine double-runner casing bleed air assembly of claim 1, wherein: the inner mounting hole is an inner threaded hole, an outer threaded part (46) is arranged at the inner end of the tracheal catheter (4), and the outer threaded part (46) is in threaded fit with the inner threaded hole.
3. The gas bleed assembly of a gas turbine double-runner casing as set forth in claim 2, wherein: a second convex ring part (45) is arranged at the inner end of the tracheal catheter (4); when the external thread part (46) is screwed on the inner mounting hole, the second convex ring part (45) abuts against the outer wall surface of the inner-layer casing (8).
4. A bleed air assembly of a double runner casing of a gas turbine engine according to one of claims 1 to 3, characterised in that: the floating sealing ring (5) is formed by splicing a left half ring (51) and a right half ring (52); both ends of the left half ring (51) and the right half ring (52) are provided with step surfaces (54) and are mutually meshed.
5. A bleed air assembly of a double runner casing of a gas turbine engine according to one of claims 1 to 3, characterised in that: the bleed air pipe (1) is provided with a flange part (11), and the flange part (11) can be fixed on the mounting ring seat (6) through the screw (3).
6. The gas turbine double-runner casing bleed air assembly of claim 5, wherein: the outer end of the tracheal catheter (4) is provided with an inner hexagonal hole (41).
7. The gas turbine double-runner casing bleed air assembly of claim 6, wherein: a locking gasket (2) is arranged between the flange part (11) and the mounting ring seat (6); the locking gasket (2) comprises an annular main body (21), an L-shaped lock tongue (23) is arranged on the inner side of the annular main body (21), and the L-shaped lock tongue (23) can be in snap fit with the hole wall of the inner hexagonal hole (41).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410479836.8A CN118088792B (en) | 2024-04-22 | 2024-04-22 | Bleed air assembly of double-layer runner casing of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410479836.8A CN118088792B (en) | 2024-04-22 | 2024-04-22 | Bleed air assembly of double-layer runner casing of gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN118088792A CN118088792A (en) | 2024-05-28 |
| CN118088792B true CN118088792B (en) | 2024-07-02 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202410479836.8A Active CN118088792B (en) | 2024-04-22 | 2024-04-22 | Bleed air assembly of double-layer runner casing of gas turbine |
Country Status (1)
| Country | Link |
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| CN (1) | CN118088792B (en) |
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| CN116124438B (en) * | 2023-02-23 | 2025-07-29 | 中国航发沈阳发动机研究所 | Double-layer case test probe mounting structure of aero-engine and assembly method thereof |
| CN115949507A (en) * | 2023-03-09 | 2023-04-11 | 中国航发四川燃气涡轮研究院 | Core machine with air-air heat exchanger and single air source for air supply |
| CN117147164B (en) * | 2023-11-01 | 2024-01-30 | 中国航发沈阳发动机研究所 | Hole detection device for double-layer casing of aero-engine |
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2024
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113864057A (en) * | 2021-10-27 | 2021-12-31 | 中国航发沈阳发动机研究所 | Air-entraining structure in double-layer casing |
| CN113958378A (en) * | 2021-10-28 | 2022-01-21 | 清华大学 | Pipeline structure penetrating through three layers of casings |
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