CN113107605A

CN113107605A - Ceramic matrix composite double-T-shaped turbine rotor blade structure

Info

Publication number: CN113107605A
Application number: CN202110490001.9A
Authority: CN
Inventors: 高希光; 周岳; 宋迎东; 张盛; 于国强; 刘晨阳
Original assignee: Nanjing University of Aeronautics and Astronautics
Current assignee: Nanjing University of Aeronautics and Astronautics
Priority date: 2021-05-06
Filing date: 2021-05-06
Publication date: 2021-07-13
Anticipated expiration: 2041-05-06
Also published as: CN113107605B

Abstract

The invention discloses a Ceramic Matrix Composite (CMCs) double-T-shaped turbine rotor blade structure, wherein the CMCs double-T-shaped turbine rotor blade is divided into a blade body-edge plate structure and an edge plate-tenon structure, the two structures are both T-shaped structures with similar forms, similar weaving processes and forms can be adopted, the weaving difficulty is low, the preparation cost can be reduced by split weaving, and the risk can be effectively controlled. The joint of the blade body and the upper edge plate in the blade body-edge plate structure is an annular small-radius arc curved surface, and the joint of the tenon in the edge plate-tenon structure and the lower edge plate is an annular small-radius arc curved surface, so that stress concentration is effectively reduced. The structure can simplify the complex structure of the blade which is difficult to weave the CMCs into a relatively simple T-shaped structure, and the formed T-shaped structures of the upper part and the lower part are favorable for the integrated weaving of the CMCs.

Description

Ceramic matrix composite double-T-shaped turbine rotor blade structure

Technical Field

The invention relates to the field of aeroengine sealing, in particular to a ceramic matrix composite turbine rotor blade structure.

Background

The ceramic matrix Composite Materials (CMCs) are materials with great application prospects in the field of aeroengines, have extremely high specific strength and specific stiffness at high temperature, are light and corrosion-resistant, and can adapt to extreme working environments in aeroengine turbines. CMCs materials are gradually applied to a tail nozzle adjusting sheet and a combustor flame tube at present, and the research on CMCs turbine guide vanes is also steadily promoted.

However, current research on CMCs turbine rotor blades has not made a breakthrough, in part because: in the process of using the CMCs turbine rotor blades, the CMCs turbine rotor blades need to be subjected to extremely high temperature and extremely complex load, and a structure which is suitable for the weaving form of the CMCs needs to be adopted to solve the bearing problem. The CMCs turbine rotor blade is difficult to weave various structures on the traditional metal blade due to the weaving process, so that the structures play a role, for example, the problem of difficult weaving transition from a blade body with a large torsion angle to a tenon is solved, parts of a complex CMCs blade structure need to be subjected to a large amount of machining after weaving, and the machining difficulty is extremely high.

The invention patent of TURBINE BLADE ASSEMBLY WITH CERAMIC MATRIX COMPOSITE COMPONENTS (patent number: US2020072065A 1) discloses a structural form of a CMCs TURBINE rotor BLADE, wherein the BLADE consists of a BLADE body-tenon structure and a platform structure forming a gas channel, and the BLADE body-tenon structure and the platform structure are arranged at intervals along the circumferential direction of an engine. The structural form adopted by the blade needs to enable the blade body-tenon structure and the platform structure to be tightly matched, the structure is complex, gaps are easy to generate, gas leakage is caused, and the assembly difficulty is increased.

The invention patent of ceramic matrix composite T-shaped turbine rotor structure (application number: 202010548722.6) discloses a non-traditional T-shaped turbine rotor structure, which adopts a split type turbine disc, and takes a blade edge plate as a bearing part, thereby effectively reducing the weight of the blade. However, the width of the rim of the turbine disk matched with the turbine blade needs to be larger than the width of the blade rim plate, and the rim plate can be wrapped in the rim plate, so that the width of the rim of the turbine disk is too large, the centrifugal force of the wheel disk can be obviously increased during working, the claw-shaped clamping groove structure is complex, and the machining amount is large.

Disclosure of Invention

In order to solve the problems of complex structure and difficult process implementation of the CMCs turbine rotor blade, the invention provides a double-T-shaped turbine rotor blade structure, which is of a T-shaped structure from top to bottom and can be beneficial to processing structures such as a blade body, a flange plate, a tenon and the like of the blade by adopting a mature plain weaving process on the premise of ensuring the mechanical property of the blade. Meanwhile, the turbine disc of the blade is simple in structure, the radius of the turbine disc is obviously smaller than that of the turbine disc adopted by the T-shaped turbine rotor blade under the condition that the sizes of blade bodies are close, the structure of the wheel rim is simple, and the overall weight reduction of the turbine disc can be realized.

In order to achieve the purpose, the invention adopts the following technical scheme:

a ceramic matrix composite double-T-shaped turbine rotor blade structure comprises a blade body-flange plate structure, a flange plate-tenon structure and a blade flange plate, wherein the blade body-flange plate structure is inverted T-shaped, a T-shaped extending part is a blade body, a transverse part is an upper flange plate, the flange plate-tenon structure is positive T-shaped, the T-shaped extending part is a tenon, the transverse part is a lower flange plate, the upper flange plate and the lower flange plate are mutually sewn to form the blade flange plate, the tenon is provided with clamping grooves at the axial symmetry position, and the clamping grooves are matched with lugs on a wheel disc to perform circumferential positioning.

Further, blade-flange structure comprises blade main part layer structure and blade outsourcing layer structure, blade main part layer structure extends for plain weave fiber cloth along the radial direction of blade, lay from the leaf basin to the blade back, lay the geometry middle plane of arranging blade in with complete fibre, make fiber cloth can not produce the hole because each cross-sectional thickness of blade is different, blade outsourcing layer structure forms the blade from outside parcel blade main part layer structure, blade outsourcing layer structure that surpasss blade main part layer structure bottom edge weaves turns over to extend to both sides and forms the top flange, it is close to 90 degrees to turn over an angle.

Furthermore, the joint of the blade body and the upper edge plate is an annular small-radius arc curved surface for reducing stress concentration.

Further, the flange-tenon structure stretches the root by the main part and spreads the layer structure and stretch the root and spread the layer and add the patch structure and constitute, the main part stretches the root and spreads the layer structure and lays along tenon direction of stretching out and stretch a layer fibre cloth, bear main tensile load, the outside fibre cloth of both sides upwards extends and presents and is close to 90 degrees the buckling, form the lower flange, the main part stretches the root and spreads the layer structure and be close to tenon one end, both sides lean on outer fibre cloth respectively the kicking out, the fibre cloth bending degree that is far away more from the root center is big more, central fibre cloth does not take place the bending, insert the fritter patch in the fibre cloth space, form the tenon tooth.

Furthermore, the tenon is of a dovetail type arc-shaped structure with an extending root, the normal direction of the cross section of the tenon is perpendicular to a connecting line from the front edge to the tail edge of the blade body, and the joint of the tenon and the lower edge plate is an annular small-radius arc curved surface for reducing stress concentration.

Further, the blade flange plate also comprises reinforcing flange plate fiber cloth, the upper flange plate and the lower flange plate are laid in an aligned mode, the reinforcing flange plate fiber cloth is laid on the upper flange plate after the blade flange plate is fixed, and the upper flange plate and the lower flange plate are reinforced and fixed.

Furthermore, the upper edge plate and the lower edge plate are subjected to interlayer sewing at the overlapped part, and the fiber cloth of the reinforced edge plate, the upper edge plate and the lower edge plate are subjected to interlayer sewing along the radius direction to reinforce the fixing strength.

Furthermore, the number of layers of the fiber cloth of the upper edge plate, the lower edge plate and the reinforcing edge plate can be different according to the process requirements, and the thickness can be adjusted.

Furthermore, the blade body outer curved surface is an envelope surface formed by an airfoil curve with special aerodynamic characteristics, and the blade edge plate is a circumferential arc curved surface thin plate with the rotation center positioned on the axis of the engine.

Compared with the prior art, the invention has the beneficial effects that:

(1) according to the CMCs turbine rotor blade, the CMCs turbine rotor blade is divided into a blade body-edge plate structure and an edge plate-tenon structure, the two structures are both T-shaped structures with similar forms, similar weaving processes and forms can be adopted, the weaving difficulty is low, the preparation cost can be reduced through split weaving, and the risk can be effectively controlled. The structure can simplify the complex structure of the blade which is difficult to weave the CMCs into a relatively simple T-shaped structure, and the formed T-shaped structures of the upper part and the lower part are favorable for the integrated weaving of the CMCs.

(2) According to the invention, the blade is split into the upper and lower split structures to be respectively woven, the problem of fiber cloth weaving transition from the blade body to the tenon does not need to be considered, and the difficulty in integrally weaving the blade can be reduced. And when only a single structure is considered, the knitting optimization can be performed in a targeted manner, and the local performance is improved.

(3) In the invention, the joint of the blade body and the upper edge plate is set to be the annular small-radius arc curved surface, and the joint of the tenon and the lower edge plate is set to be the annular small-radius arc curved surface, so that the stress concentration is effectively reduced.

(4) In the invention, a plurality of layers of bent fiber cloth extend from the joint of the upper edge plate and the lower edge plate, are folded and aligned to the joint and are sewn among layers, an effective airflow channel can be formed, meanwhile, the rigidity requirement required by mutual collision and abrasion of the edge plates between the blades and support and the process feasibility of CMCs materials are considered when the fiber cloth is laid, the thickness of the edge plates can be adjusted, and the split operation process is simple.

Drawings

FIG. 1: the three-dimensional schematic diagrams of the CMCs double-T-shaped turbine rotor blade structure at different angles;

FIG. 2: a blade body-flange structure and a flange-tenon structure are schematically shown;

FIG. 3: a blade body-flange structure layering schematic diagram;

fig. 4(a) and 4 (b): a layer laying schematic diagram of a flange plate-tenon structure;

FIG. 5: a schematic diagram of a fiber cloth layer of the reinforced flange plate;

FIG. 6: CMCs double T turbine rotor blade weaving structure schematic diagram.

Wherein: a blade body-edge plate structure-1, an edge plate-tenon structure-2, a blade edge plate-3, a reinforced edge plate fiber cloth-4, a clamping groove-5, a blade body-11, an upper edge plate-12, a tenon-21, a lower edge plate-22, a patch-23 and a tenon-24.

Detailed Description

The invention will be further explained with reference to the drawings.

According to the attached drawings, the CMCs double-T-shaped turbine rotor blade structure is composed of an upper T-shaped structure and a lower T-shaped structure, wherein the inverted T-shaped structure is a blade body-edge plate structure 1, the positive T-shaped structure is an edge plate-tenon structure 2, the radial extending parts of the T-shaped structures are a blade body 11 and a tenon 21 of a blade respectively, in order to form an effective airflow channel, a plurality of layers of bent fiber cloth extend from the lower part of the blade body and the upper part of the tenon to form an upper edge plate 12 and a lower edge plate 22 respectively, and the upper edge plate and the lower edge plate are folded and aligned at a joint and are sewn. The thickness can be adjusted by considering the rigidity requirement required by mutual collision and abrasion of the edge plates between the blades and support and the process feasibility of the CMCs material during laying. The structure can simplify the complex structure of the blade which is difficult to weave the CMCs into a relatively simple T-shaped structure, and the formed T-shaped structures of the upper part and the lower part are favorable for the integrated weaving of the CMCs.

The blade body-edge plate structure 1 is composed of two types of laying layer structures, namely a blade body main body laying layer structure and a blade body outer wrapping laying layer structure. The blade body main part is spread layer structure design and is: the plain weave fiber cloth extends along the leaf height direction and is laid from the leaf basin to the leaf back. In order to ensure the integrity of each fiber cloth laying layer and avoid the generation of holes of the fiber cloth due to different thicknesses of each section of the blade body, the most complete fiber cloth is arranged on the geometric middle surface of the blade body. The blade body outer covering layer structure is divided into two parts, the blade body main body layer is covered from the outside to the inside, and the edge of the bottom of the blade body is folded and woven to form an upper edge plate structure.

The layer design of the flange plate-tenon structure 2 is in a form that a main body extends a root layer structure and a patch is added between the root layer structures. The main part stretches the root and spreads the layer structure design and be: the extended fiber cloth extending from the flange plate along the radial direction is used as the extended root layer main body of the flange plate-tenon part to bear the main tensile load. At the lowest end of the root extending layer close to the tenon 21, part of the fiber cloth is bent towards the tenon tooth 24 direction, and the bending degree of the fiber cloth which is farther away from the center of the root extending layer is larger, so that the center fiber cloth is not bent. And small patches 23 are inserted into the gaps of the fiber cloth to form a tenon tooth 24 structure. The outer fiber cloth positioned at the two sides of the tenon 21 is bent by nearly 90 degrees at the contact position of the double-T-shaped structure, and is spliced and aligned with the fiber cloth turned over in the blade body outer-wrapping layer structure of the blade body-edge plate part 1, and interlayer sewing is carried out, so that the blade body-edge plate structure 1 and the edge plate-tenon structure 2 are fixedly connected. The clamping grooves 5 which are axially symmetrical are machined at the tenon and are matched with the convex blocks on the turbine disc for circumferential positioning.

Aligning and interlaminar sewing the fiber cloth of the upper edge plate 12 and the lower edge plate 22, laying a layer of reinforced edge plate fiber cloth 4 on the fiber cloth, reinforcing and fixedly connecting the sewing structures of the upper edge plate 12 and the lower edge plate 22 to form a blade edge plate, and interlaminar sewing in the radius direction to reinforce the connection strength of the upper part and the lower part.

The curved surface of the blade body 11 is an envelope surface formed by an airfoil curve with special aerodynamic characteristics. The blade flange plate 3 is a circumferential arc curved surface thin plate with the thickness of 1mm-2mm and the rotation center positioned on the axis of the engine. The joint of the blade body 11 and the upper edge plate 12 is an annular small-radius arc curved surface for reducing stress concentration. The tenon 21 is a dovetail type arc structure with an extending root, the middle part is provided with a circumferential positioning clamping groove 5, and the normal direction of the cross section of the tenon 21 is approximately vertical to the connecting line from the front edge to the tail edge of the blade body 11. The joint of the tenon 21 and the lower edge plate 22 is an annular small-radius arc curved surface for reducing stress concentration.

The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims

1. The utility model provides a two T turbine rotor blade structures that appear of ceramic matrix composite which characterized in that: constitute by blade body-flange structure (1), flange-tenon structure (2) and blade flange (3), blade body-flange structure (1) for falling T shape, T shape stretches out the part and is blade body (11), horizontal part is last flange (12), flange-tenon structure (2) for positive T shape, T shape stretches out the part and is tenon (21), horizontal part is lower flange (22), last flange (12) and lower flange (22) sew up each other and constitute blade flange (3), tenon (21) be provided with draw-in groove (5) in axial symmetry department, draw-in groove (5) and the lug cooperation on the rim plate carry out circumference location.

2. The ceramic matrix composite double T-shaped turbine rotor blade structure of claim 1, wherein: blade-border structure (1) lay the layer structure by blade main part and constitute with blade outsourcing, blade main part lay the layer structure and extend along the radial direction of blade (11) for plain weave fiber cloth, lay to the blade back from the leaf basin, lay the geometry midplane of arranging blade (11) in with complete fibre, make fiber cloth can not produce the hole because each section thickness of blade (11) is different, blade outsourcing lay the layer structure from outside parcel blade main part lay the layer structure and form blade (11), the blade outsourcing that exceeds blade main part lay the layer structure bottom edge turns over to fold to weave and extend to both sides and form edge board (12), turns over an angle and is close to 90 degrees.

3. The ceramic matrix composite double T-shaped turbine rotor blade structure of claim 2, wherein: the joint of the blade body (11) and the upper edge plate (12) is an annular small-radius arc curved surface for reducing stress concentration.

4. The ceramic matrix composite double T turbine rotor blade structure of claim 3 wherein: marginal plate-tenon structure (2) stretch the root by the main part and spread the layer structure and stretch the root and spread the layer and add the patch structure and constitute, the main part stretches the root and spreads the layer structure and stretch a layer fibre cloth along tenon (21) direction of stretching out, bear main tensile load, outside fibre cloth of both sides upwards extends and presents and is close to 90 degrees buckles, form lower marginal plate (22), the main part stretches the root and spreads the layer structure and is close to tenon (21) one end, both sides lean on outer fibre cloth respectively outwardly curved, the fibre cloth bending degree far away from the root center is big more, central fibre cloth does not take place the bending, insert the fritter patch between fibre cloth space, form tenon tooth (24).

5. The ceramic matrix composite double T turbine rotor blade structure of claim 4 wherein: the tenon (21) is of a dovetail type arc-shaped structure with an extending root, the normal direction of the cross section of the tenon (21) is perpendicular to a connecting line from the front edge to the tail edge of the blade body (11), and the joint of the tenon (21) and the lower edge plate (22) is an annular small-radius arc curved surface for reducing stress concentration.

6. The ceramic matrix composite double T-shaped turbine rotor blade structure of claim 1, wherein: the blade flange plate (3) further comprises reinforcing flange plate fiber cloth (4), the upper flange plate (12) and the lower flange plate (22) are arranged in an aligned mode, the reinforcing flange plate fiber cloth (4) is arranged on the upper flange plate after the blade flange plate is fixed, and the upper flange plate (12) and the lower flange plate (22) are reinforced and fixed.

7. The ceramic matrix composite double T turbine rotor blade structure of claim 6 wherein: the upper edge plate (12) and the lower edge plate (22) are sewed at the overlapped position between layers, and the reinforced edge plate fiber cloth (4) is sewed with the upper edge plate (12) and the lower edge plate (22) along the radius direction between layers to reinforce the fixing strength.

8. The ceramic matrix composite double T turbine rotor blade structure of claim 6 wherein: the number of layers of the upper edge plate (12), the lower edge plate (22) and the reinforcing edge plate fiber cloth (4) can be adjusted according to the process requirements.

9. The ceramic matrix composite double T-shaped turbine rotor blade structure of claim 1, wherein: the blade body (11) is characterized in that the outer curved surface is an envelope surface formed by airfoil curves with special aerodynamic characteristics, and the blade edge plate (3) is a circumferential arc curved surface thin plate with a rotation center positioned on the axis of an engine.