CN113503190B - Aeroengine stator blade edge plate sealing strip, stator blade and sealing structure - Google Patents
Aeroengine stator blade edge plate sealing strip, stator blade and sealing structure Download PDFInfo
- Publication number
- CN113503190B CN113503190B CN202111066012.0A CN202111066012A CN113503190B CN 113503190 B CN113503190 B CN 113503190B CN 202111066012 A CN202111066012 A CN 202111066012A CN 113503190 B CN113503190 B CN 113503190B
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- stator blade
- sealing strip
- engine
- flange
- aeroengine
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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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gasket Seals (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model provides an aeroengine stator blade flange obturating strip for install the flange surface from the stator blade outside, with the gap between the adjacent flange of closure, including being used for installing the wing section on flange surface, including the locking structure in the wing section, the wing section corresponds adjacent stator blade flange and distributes in the obturating strip both sides. The stator blade comprises a flange plate, wherein grooves matched with sealing strips in a shape mode are formed in the edges of the outer side surfaces of two sides of the flange plate, and a locking matching structure is provided. The utility model provides a structure of obturating, includes sealing strip and stator blade, and sealing strip installs the surface at stator blade flange, and its installation need not to disassemble the engine with dismantling, and the structure is light, and the maintenance is simple, has reduced engine maintenance cost.
Description
Technical Field
The invention relates to the field of aero-engines, in particular to a sealing strip for an aero-engine stator blade flange plate, a stator blade and a sealing structure.
Background
The basic principle of the work of a turbofan engine with a high bypass ratio adopted by a modern civil aviation passenger plane is that external air flow is pressurized by a fan pressurizing rotor blade after being sucked, a small part of air flow enters an inner bypass combustion chamber and is mixed with fuel oil to participate in combustion to provide power for the engine, and a large part of air flow flows to the tail of the engine after passing through a circle of circumferential outer bypass stator blades and is discharged after being mixed with inner bypass air flow to provide main thrust for the forward movement of the engine. Wherein, the outer stator blade both ends of culvert are connected with machine casket and outer loop respectively, play the effect of support and water conservancy diversion.
The bypass stator blade structurally comprises a blade body, a flange plate and an installation edge, wherein one end of the flange plate is circumferentially installed on the casing, an inner duct is formed inside the flange plate circumferentially arranged, and an outer duct is formed outside the flange plate. Due to part tolerances or assembly reasons, there is often a circumferential gap between the platform of adjacent blades. In the working process of the engine, the booster stage rotor boosts the air flow of the inner duct, so that the working pressure of the inner duct is higher than that of the outer duct. And because the stator blade flange plate circumferential clearance's existence, the inner duct air current can outwards duct leakage, has reduced the work efficiency and the stability of engine, has produced adverse effect to fuel economy. A
Currently, there are two main types of solutions to this problem. One type eliminates circumferential gaps by improving the machining and assembling precision of stator blades, but the method has high cost, high machining difficulty, high product rejection rate and low assembling efficiency, and is difficult to adopt for civil airliners. Another type of seal prevents air leakage by filling the circumferential gap of the stator blade rim plate with a sealing strip. In the prior art, a U-shaped groove is formed in a contact surface of adjacent flanges of a stator blade, and a sealing strip is inserted into the U-shaped groove from back to front along the axial direction of an engine to realize sealing. However, the scheme has certain requirements on the thickness of the flange plate, the weight of the engine is increased, the sealing strip is installed in an axial insertion mode, the engine needs to be disassembled, and the maintenance difficulty and the maintenance cost of the engine are greatly increased.
Disclosure of Invention
The invention provides a sealing strip for a stator blade edge plate of an aero-engine, a stator blade and a sealing structure, and aims to solve the problem of air leakage of an inner duct caused by poor sealing of the stator blade edge plate when a civil turbofan engine works.
According to an aspect of an embodiment of the invention, an aeroengine stator blade flange sealing strip is used for being installed between adjacent stator blade flanges of an aeroengine and filling a circumferential gap between the adjacent stator blade flanges, wherein: the sealing strip is used for being installed on the outer side surface of the adjacent stator blade flange plate, specifically, the outer side refers to one side of the flange plate, far away from the axis of the engine in the radial direction of the engine, of the stator blade in the installation position; the sealing strip has an airfoil portion for mounting on an outboard surface of the platform; the wing-shaped part is provided with a locking structure; the sealing strips are respectively distributed with the airfoil parts at two sides corresponding to the adjacent stator blade flanges.
Preferably, the cross section of the stator blade flange plate sealing strip is rectangular.
Preferably, two sides of the stator blade flange plate sealing strip are respectively provided with 2-3 spaced airfoil parts in a protruding mode.
Preferably, the outer side surface of the stator blade flange at the mounting position of the sealing strip of the stator blade flange is provided with a hole, and the locking structure is an elastic barb which can pass through the hole on the outer side surface of the stator blade flange.
Optionally, the shape of the elastic barb is a hemispherical protrusion, a radial truncated cone-shaped protrusion, a conical protrusion or a T-shaped boss.
According to another aspect of an embodiment of the present invention, an aircraft engine stator blade comprises a platform, wherein: the outer surfaces of the edges of the two sides of the flange plate are respectively provided with a groove, so that a pair of mounting grooves can be defined between the adjacent flange plates of two adjacent stator blades, and specifically, the outer surface refers to the surface of one side of the flange plate, which is far away from the axis of an engine in the radial direction of the engine, of the stator blade at the mounting position; the mounting groove is used for mounting the aeroengine stator blade edge plate sealing strip provided by the invention, is matched with the aeroengine stator blade edge plate sealing strip along the shape, and is provided with a locking matching structure for mounting and fixing the aeroengine stator blade edge plate sealing strip.
Preferably, the locking fit structure of the stator blade is a through hole which is arranged in the mounting groove and penetrates through the flange plate.
According to another aspect of the embodiment of the invention, the sealing structure for the stator blade of the aero-engine comprises the stator blade and a sealing strip, wherein the sealing strip is the sealing strip for the edge plate of the stator blade of the aero-engine, the stator blade is the stator blade of the aero-engine, the sealing strip is arranged between the adjacent edge plates of the adjacent stator blades for sealing, the sealing strip is arranged from the outer side to the inner side of the edge plates, and the sealing strip is locked by matching of the locking structure and the locking matching structure.
The sealing strip provided by the invention has a sealing effect on a gap between adjacent stator blade flanges of the engine, solves the problem of gas leakage from an inner duct to an outer duct of the engine, and improves the working efficiency and stability of the engine. The mounting position of the sealing strip is located on the outer side surface of the stator blade flange plate, a U-shaped groove does not need to be formed in the flange plate, the thickness of the flange plate is reduced, the effect of reducing the weight of a part is achieved, and the processing difficulty of the part is reduced. The sealing strip is installed from the outer side of the flange plate, the engine does not need to be disassembled, maintenance and replacement are simple, and additional complex maintenance procedures are avoided.
Drawings
FIG. 1 is a schematic structural view of a sealing strip of an engine stator blade edge plate;
FIG. 2 is a schematic view of a section A-A of a sealing strip of a stator blade platform of the engine shown in FIG. 1;
FIG. 3 is a schematic view of an engine stator blade configuration;
FIG. 4 is a schematic view of the assembled relationship of the stator blades and the sealing strips of the engine;
FIG. 5 is a schematic cross-sectional view B-B of the stator vane platform and seal of the engine of FIG. 4;
FIG. 6 is a schematic illustration of a section C-C of the engine stator vane platform and seal strip of the embodiment of FIG. 4;
FIG. 7 is a schematic cross-sectional view C-C of a stator vane platform and seal of the engine of the alternate embodiment of FIG. 4;
FIG. 8 is a schematic cross-sectional view C-C of a stator vane platform and seal strip of the engine of the further embodiment of FIG. 4.
Reference signs mean:
1-sealing strip; 2-an airfoil section; 3-a locking structure; 4-stator blades; 5-a flange plate; 6-mounting grooves; 7-locking the fitting structure; 8-gap.
It is to be expressly understood that the above description of the drawings is intended as a detailed description of the concepts of the invention and is not intended as a definition of the limits of the embodiments of the invention. The figures only show schematically the structure to which the invention relates, and not to scale strictly the complete structure of an aircraft engine, details of the relevant parts not relevant to the invention being omitted.
Detailed Description
The invention is described in further detail below with reference to the figures and examples.
FIG. 1 shows a schematic structural diagram of a sealing strip of an aeroengine stator blade flange, wherein the sealing strip 1 is used for being installed on the outer side surface of an adjacent engine stator blade flange, the outer side refers to one side of the flange of the stator blade in the installation position, which is far away from the axis of an engine in the radial direction of the engine, and the sealing strip 1 comprises a sealing strip body in a long and thin strip shape and a convex airfoil section 2, and two sides of the sealing strip 1 are respectively provided with 2 airfoil sections 2. The length of the body of the sealing strip is the same as that of the engine stator blade flange plate on which the sealing strip is installed. As shown in FIG. 2, a locking structure 3 is arranged on the wing section 2, the locking structure 3 is a hemispherical convex elastic barb, 3 elastic barbs 3 are arranged on each wing section, and the cross section of the sealing strip 1 is rectangular.
According to another embodiment, the cross section of the sealing strip 1 is semicircular.
According to another embodiment, the locking structure 3 is shaped as a radial circular boss, a conical protrusion or a T-shaped boss.
According to another embodiment, the cross-sectional shape of the airfoil 2 is trapezoidal and the locking structure 3 is the wider base angle of the trapezoidal airfoil 2.
According to a further embodiment, the sealing strip 1 is provided with 3 pairs of airfoils 2.
As shown in FIG. 3, the stator blade of the aero-engine comprises a blade 4, one end of the blade is connected with an outer ring of the engine through a mounting edge, the other end of the blade is provided with a flange 5, the stator blade is circumferentially mounted on an intermediate casing of the engine through the flange 5, an outer duct of the engine is arranged on the outer side of the flange 5, and an inner duct of the engine is arranged on the inner side of the flange 5. After air pressurized by the fan rotor enters the engine, part of the air enters the inner duct to participate in combustion in the combustion chamber to provide power for the engine, and the other part of the air enters the outer duct and is sprayed out from the tail part of the engine to provide main thrust, wherein the pressure of the inner duct is higher than that of the outer duct, so that a sealing structure is required to be arranged between adjacent flanges to prevent air leakage. Be provided with recess 6 on the outside surface of flange 5, recess 6 on the adjacent stator blade is injectd mated mounting groove for the installation of sealing strip 1, recess 6 and sealing strip 1 follow shape cooperation. The corresponding position on the groove 6 is provided with a locking matching structure 7, which comprises a through hole for matching the installation of the wing section 2 and the locking structure 3.
The installation relation of a sealing structure consisting of the sealing strip 1 and the stator blades is shown in figure 4, the sealing strip 1 is installed in a groove 6 on the outer side surface of a flange plate 5, and as shown in figure 5, the sealing strip 1 plays a sealing role in a circumferential gap 8 between adjacent flange plates; as shown in fig. 6, the locking structure 3 passes through the through hole in the locking matching structure 7, and the sealing strip 1 and the flanges 5 of two adjacent stator blades are respectively fixed to prevent the sealing strip from falling off. The installation operation of the sealing strip 1 is carried out on the outer side of the stator blade of the engine, the sealing strip 1 is filled into the groove 6 of the adjacent stator blade, and the locking structure 3 on the wing section 2 penetrates through the through hole in the locking matching structure 7 to be locked and fixed. When the sealing strip is repaired and replaced, the disassembly operation is also carried out on the outer side of the stator blade of the engine, and the sealing strip 1 is pried out of the groove 6 to finish the disassembly. The operation of the installation of the sealing strip 1 and the dismantlement does not need to be disassembled to the engine, the operating space of the original structure of the engine can be fully utilized, unnecessary complex maintenance procedures are reduced, the cost is saved, and the efficiency is improved. Meanwhile, because the U-shaped groove does not need to be formed on the side surface of the edge plate 5 of the adjacent stator blade, the thickness of the edge plate 5 is reduced, and the weight of the engine is further reduced.
According to another embodiment, as shown in fig. 7, the wing section 2 of the sealing strip 1 is trapezoidal, the locking structure 3 is an extended trapezoidal bottom corner, and the locking matching structure 7 on the flange plate 5 is a trapezoidal groove matched with the trapezoidal wing section 2 in a following manner. When the sealing strip is installed, the sealing strip 1 is filled into the groove 6 from the outer side surface of the flange plate 5, a circumferential gap 8 between adjacent flange plates is sealed, the wider trapezoidal base angle of the wing part 2 forms a locking structure 3 and is clamped in a locking matching structure 7 of the same trapezoidal groove 6, and the sealing strip is fixed relative to the stator blade flange plate. When the sealing strip is disassembled, the sealing strip 1 is pried out of the groove 6 from the outer side of the flange plate 5, and then the disassembly can be completed. The operation of the installation of the sealing strip 1 and the dismantlement does not need to be disassembled to the engine, the operating space of the original structure of the engine can be fully utilized, unnecessary complex maintenance procedures are reduced, the cost is saved, and the efficiency is improved.
According to another embodiment, as shown in fig. 8, the wing section of the sealing strip 1 is trapezoidal, the locking structure 3 is an extended trapezoidal bottom corner, and the locking matching structure 7 on the flange plate 5 is an inverted slope matched with the trapezoidal wing section 2 in a conformal manner. When the sealing strip is installed, the sealing strip 1 is filled into the groove 6 from the outer side surface of the flange plate 5, a sealing effect is achieved on a circumferential gap 8 between adjacent flange plates, the wider trapezoidal base angle of the wing section 2 forms a locking structure 3 and is buckled into the lower surface of the inverted inclined surface 7 of the groove 6, and the sealing strip is fixed relative to the stator blade flange plate. When the sealing strip is disassembled, the sealing strip 1 is pried out of the groove 6 from the outer side of the flange plate 5, and then the disassembly can be completed. The operation of the installation of the sealing strip 1 and the dismantlement does not need to be disassembled to the engine, the operating space of the original structure of the engine can be fully utilized, unnecessary complex maintenance procedures are reduced, the cost is saved, and the efficiency is improved.
It should be understood that the above description of the embodiments is intended to provide further detailed description of the technical solutions and inventive concepts of the present invention, and to provide an understanding to those skilled in the art. The contents of the examples are not intended to limit the embodiments of the present invention, and it is within the scope of the claims of the present invention to modify the specific structure or substitute the equivalent, or to combine the embodiments without conflict between the technical solutions.
Claims (8)
1. The utility model provides an aeroengine stator blade reason board sealing strip for install between aeroengine adjacent stator blade reason board, its characterized in that:
the sealing strip is used for being installed on the outer side surface of the adjacent stator blade flange plate, wherein the outer side refers to one side, away from the axis of the engine in the radial direction of the engine, of the flange plate of the stator blade in the installation position;
the sealing strip has an airfoil portion for mounting on an outboard surface of the platform;
the wing-shaped part is provided with a locking structure;
the sealing strips are respectively distributed with the airfoil parts at two sides corresponding to the adjacent stator blade flanges.
2. The aero-engine stator blade edge plate seal strip as defined in claim 1, wherein the seal strip is rectangular in cross-section.
3. The aero-engine stator blade edge plate seal strip as claimed in claim 1, wherein two sides of the seal strip are respectively provided with 2-3 spaced apart airfoil portions in a protruding manner.
4. The aero engine stator blade rim plate seal strip of claim 1 wherein the locking structure is a resilient barb that is insertable through a hole in an outer side surface of the stator blade rim plate.
5. The aero engine stator blade rim plate seal strip of claim 4 wherein the resilient barb is shaped as a hemispherical protrusion, a radial circular boss, a conical protrusion, or a T-shaped boss.
6. An aeroengine stator blade, includes the flange, its characterized in that:
the outer surfaces of the edges of the two sides of the flange plate are respectively provided with a groove, so that a pair of mounting grooves can be defined between the adjacent flange plates of two adjacent stator blades, wherein the outer surface refers to the surface of one side of the flange plate, far away from the axis of an engine in the radial direction of the engine, of the stator blade in the mounting position;
the mounting groove is used for being matched with the airfoil part of the aeroengine stator blade edge plate sealing strip according to any one of claims 1 to 5 in a shape following mode, and a locking matching structure is provided for mounting and fixing the aeroengine stator blade edge plate sealing strip.
7. An aircraft engine stator vane according to claim 6, wherein said locking engagement formation is a through hole provided through said platform in said mounting slot.
8. An aeroengine stator blade sealing structure, including stator blade and sealing strip, characterized in that, sealing strip is as in any one of claims 1-5 aeroengine stator blade flange sealing strip, the stator blade is as in claim 6 or 7 the aeroengine stator blade, adjacent between the adjacent flange of stator blade by sealing strip seals, sealing strip from the outside of flange to inboard installation, and by locking structure with the cooperation lock of locking cooperation structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111066012.0A CN113503190B (en) | 2021-09-13 | 2021-09-13 | Aeroengine stator blade edge plate sealing strip, stator blade and sealing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111066012.0A CN113503190B (en) | 2021-09-13 | 2021-09-13 | Aeroengine stator blade edge plate sealing strip, stator blade and sealing structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113503190A CN113503190A (en) | 2021-10-15 |
| CN113503190B true CN113503190B (en) | 2022-02-15 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111066012.0A Active CN113503190B (en) | 2021-09-13 | 2021-09-13 | Aeroengine stator blade edge plate sealing strip, stator blade and sealing structure |
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| CN (1) | CN113503190B (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100482928C (en) * | 2004-02-18 | 2009-04-29 | 翔鹰宇航有限责任公司 | Seal device |
| EP2642080A1 (en) * | 2012-03-20 | 2013-09-25 | Alstom Technology Ltd | Turbomachine blade and corresponding operating method |
| CN105531444A (en) * | 2013-07-25 | 2016-04-27 | 西门子公司 | Sealing arrangement for a turbomachine |
| EP3653844A1 (en) * | 2018-11-15 | 2020-05-20 | Siemens Aktiengesellschaft | Strip seal, annular segment and method for a gas turbine |
-
2021
- 2021-09-13 CN CN202111066012.0A patent/CN113503190B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100482928C (en) * | 2004-02-18 | 2009-04-29 | 翔鹰宇航有限责任公司 | Seal device |
| EP2642080A1 (en) * | 2012-03-20 | 2013-09-25 | Alstom Technology Ltd | Turbomachine blade and corresponding operating method |
| CN105531444A (en) * | 2013-07-25 | 2016-04-27 | 西门子公司 | Sealing arrangement for a turbomachine |
| EP3653844A1 (en) * | 2018-11-15 | 2020-05-20 | Siemens Aktiengesellschaft | Strip seal, annular segment and method for a gas turbine |
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| Publication number | Publication date |
|---|---|
| CN113503190A (en) | 2021-10-15 |
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