CN112267917B - Fiber preform and ceramic matrix composite turbine outer ring - Google Patents
Fiber preform and ceramic matrix composite turbine outer ring Download PDFInfo
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- CN112267917B CN112267917B CN202010988304.9A CN202010988304A CN112267917B CN 112267917 B CN112267917 B CN 112267917B CN 202010988304 A CN202010988304 A CN 202010988304A CN 112267917 B CN112267917 B CN 112267917B
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- outer ring
- ceramic matrix
- turbine outer
- matrix composite
- turbine
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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
- F01D25/005—Selecting particular materials
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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
- F01D25/30—Exhaust heads, chambers, or the like
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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
Abstract
The invention provides a fiber preform for an outer ring of a turbine, which comprises a pi-shaped part on an upper layer, a C-shaped part matched with the pi-shaped part and an arc-shaped part arranged on a lower layer. The fiber preform for the outer ring of the turbine is simple and convenient in process formability, suitable for various raw material forms such as two-dimensional fiber cloth and unidirectional tape prepreg, free of a three-dimensional weaving complex forming process, suitable for mass production and application, consistent in quality stability, low in manufacturing cost and short in period.
Description
Technical Field
The invention belongs to the field of aero-engines, and particularly relates to a fiber preform and a ceramic matrix composite turbine outer ring.
Background
With the increase of thrust-weight ratio of advanced aeroengines, heat end components such as tail pipes, combustion chambers, turbines and the like have increasingly urgent requirements on ceramic matrix composite materials with light weight, high temperature resistance, long service life and oxidation resistance. The outer ring of a high-pressure turbine of an aircraft engine is directly contacted with high-temperature hot gas, bears large thermal stress and is a typical hot-end stator component of the engine. The outer ring of the existing metal turbine adopts equiaxial casting high-temperature alloy or directional solidification single crystal high-temperature alloy, and the problems of ablation, deformation, insufficient temperature resistance and the like often occur in the test process. The ceramic-based composite material is adopted to replace high-temperature alloy to prepare the outer ring of the turbine, so that the temperature resistance of parts can be improved by about 300 ℃, the phenomenon of local ultra-mild ablation deformation of the outer ring of the conventional metal turbine is solved, and the consumption of cold air led out from the gas compressor is reduced (no cold air is used); the weight of the structure is reduced by 50-70%, gap control is facilitated, the diffusion of gas heat to a casing is reduced, the turbine efficiency is improved, and the oil consumption rate of an engine is reduced.
In order to improve engine performance, research on ceramic matrix composites in hot end parts of military and civil engines has been developed in europe, the usa and japan, and many densification processes have been developed, and the mainstream processes include Chemical Vapor deposition (CVI), Precursor Impregnation and Pyrolysis (PIP), and Reactive Melt Infiltration (RMI). The ceramic matrix composite turbine outer ring has been realized to realize batch production application on commercial engines such as Leap, GE9x and the like, the structural weight of the engine is reduced, and the oil consumption is reduced by more than 1.5%. The technology research and the application examination research of CVI, PIP, RMI and the like are also developed at home aiming at ceramic matrix composite sealing sheets/adjusting sheets, flame tubes, turbine outer rings and other hot end components for aero-engines.
The structure of the ceramic matrix composite member and the fiber prefabricated body thereof have the integrated design characteristic, the fiber is used as the reinforcement of the composite material and is the main bearing phase of the composite material, and the structure and the performance of the fiber prefabricated body greatly influence the performance of the composite material and the member. The ceramic matrix composite has strong designability characteristic, the general fiber preform structure is divided into a unidirectional tape, 2D and 3D and a combined connection structure, wherein the 2D preform structure is simplest, the process realizability is good, the fiber preform structure is suitable for forming thin-wall parts, but the difficulty for forming components with complex structures and large thickness dimension is higher, the interlayer strength (Z direction) is lower, the interlayer strength can be improved and the complex components can be formed through the appearance structure design of the components, the 3D weaving and combined connection of the preforms and other forms, and the in-plane performance can be influenced.
The outer ring of the turbine is positioned on a turbine casing corresponding to the blade tip of a high-pressure turbine rotor blade of the aircraft engine, is directly contacted with high-temperature gas during working, and needs to bear certain mechanical excitation force and pneumatic load. Once the outer ring of the turbine is broken, the turbine blades rotating at high speed can be damaged, and serious faults are caused. The turbine outer ring prefabricated body structure connected by the pin combination has lower interlayer tensile strength (Z direction), the pins are easy to generate stress concentration under the action of vibration stress, fiber bearing force does not exist between laminates, failure modes of pin fracture and layered cracking damage occur, and the requirements of engine engineering application are not met. The ceramic matrix composite turbine outer ring urgently needs a fiber preform with high interlayer strength, high vibration reliability and good process realizability to meet the application requirements of engine engineering.
Disclosure of Invention
In order to solve the problems, the invention provides a fiber preform and a ceramic matrix composite turbine outer ring, which are used for improving the interlayer strength of the turbine outer ring, solving the problems that the existing split preform is easy to generate delamination cracking damage and the 3D weaving process is complex, improving the process realizability of the ceramic matrix composite turbine outer ring, and meeting the structural strength design and use requirements of the aircraft engine turbine outer ring.
The invention aims to provide a fiber preform, which comprises a pi-shaped part on an upper layer, a C-shaped part matched with the pi-shaped part and an arc-shaped part arranged on a lower layer.
The fiber preform provided by the invention is also characterized in that the pi-shaped part, the C-shaped part and the arc-shaped part are made of unidirectional tape fiber prepreg.
The fiber preform for the turbine outer ring provided by the invention is also characterized in that the ply of the unidirectional tape fiber prepreg comprises a ply angle selected from 0 degrees, 45 degrees and 90 degrees.
The fiber preform provided by the invention also has the characteristic that the pi-shaped piece, the C-shaped piece and the arc-shaped piece are made of two-dimensional warp and weft cloth.
The fiber preform provided by the invention is also characterized in that the two-dimensional warp and weft cloth is sewed through fibers.
The fiber preform provided by the invention is also characterized in that the number ratio of the pi-shaped pieces to the C-shaped pieces is 1: 2-2: 1.
the fiber preform provided by the present invention is also characterized in that the fiber comprises alumina fiber or silicon carbide fiber.
Another object of the present invention is to provide an outer ring of a CMC turbine that is fabricated from any of the above CMC fiber preforms by a CVI, PIP, RMI densification process.
The ceramic matrix composite turbine outer ring provided by the invention is also characterized in that the turbine outer ring is in an inverted pi shape, one side of a lower bottom plate of the turbine outer ring is provided with a recess, and the other side of the lower bottom plate of the turbine outer ring is provided with a bulge matched with the recess.
The outer ring of the ceramic matrix composite turbine provided by the invention is also characterized in that the surface of the lower bottom plate of the outer ring of the turbine is provided with grooves and blind holes.
The ceramic matrix composite turbine outer ring provided by the invention has the characteristics that the blind hole is cylindrical or circular, the diameter is less than or equal to 1.5mm, and the hole depth is 0.2-0.5 mm.
The ceramic matrix composite turbine outer ring provided by the invention is also characterized in that the grooves are straight lines with different angles of 15 degrees, 30 degrees, 45 degrees and the like.
Compared with the prior art, the method has the following beneficial effects
1. The fiber preform for the outer ring of the turbine is simple and convenient in process formability, suitable for various raw material forms such as two-dimensional fiber cloth and unidirectional tape prepreg, free of a three-dimensional weaving complex forming process, suitable for mass production and application, consistent in quality stability, low in manufacturing cost and short in period.
2. The turbine outer ring provided by the invention is made of an integral fiber prefabricated body and is used as an integral structure, so that the fiber bearing force is arranged in the interlayer direction of the turbine outer ring, the strength of a component between layers and the reliability of the component are improved, the problem of layered cracking of the existing split prefabricated body due to insufficient interlayer strength is solved, the turbine outer ring is a ceramic matrix composite turbine outer ring, and the thin-wall structure can meet the working condition requirements of the engine on strength, assembly, sealing and the like, can be suitable for densification forming and processing of the ceramic matrix composite, and meets the strength design and use requirements of the engine.
Drawings
FIG. 1 is a schematic structural diagram of a ceramic matrix composite turbine outer ring preform;
FIG. 2 is a schematic view of a seaming of a ceramic matrix composite turbine outer ring fiber preform;
FIG. 3 is a schematic view of an outer ring structure of a ceramic matrix composite turbine;
FIG. 4 is a schematic view of a ceramic matrix composite turbine outer ring seal structure;
FIG. 5 is a schematic view of a blind hole of a lower bottom plate of an outer ring of a ceramic matrix composite turbine;
FIG. 6 is a schematic view of a groove in a lower base plate of an outer ring of a ceramic matrix composite turbine;
FIG. 7 is a schematic view of an abradable coating for a ceramic matrix composite turbine outer ring lower base plate.
Detailed Description
In order to make the technical means, the original characteristics, the achieved objects and the effects of the present invention easily understood, the fiber preform and the cmc outer ring provided in the present invention are specifically described in the following embodiments with reference to the accompanying drawings.
In the description of the embodiments of the present invention, it should be understood that the terms "central," "longitudinal," "transverse," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientations and positional relationships indicated in the drawings, which are only for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the device or element so referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit to a number of indicated technical features. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the invention, "a plurality" means two or more unless otherwise specified.
The terms "mounted," "connected," and "coupled" are to be construed broadly and may, for example, be fixedly coupled, detachably coupled, or integrally coupled; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art through specific situations.
As shown in fig. 1 to 7, the turbine outer ring is assembled on a metal turbine casing and forms rotor and stator matching with the blade tips of turbine rotor blades, in order to reduce thermal stress and size deformation, the ceramic matrix composite turbine outer ring is designed into a segmented fan-shaped structure and assembled into a whole ring, lugs at two ends are assembled on the casing, the size and the gap of an assembly position are designed, and the assembly requirements of an engine and the thermal expansion matching requirements of the ceramic matrix composite and metal are ensured. According to the structural stress working condition of the outer ring of the turbine, the appearance structure design of the outer ring of the ceramic matrix composite turbine is developed, structures such as thick plates, reinforcing ribs and air film holes are omitted, the section thickness of each part of the outer ring of the turbine is reduced, the outer ring of the turbine is designed into a circular arc structure with excessive roundness, and the outer ring of the turbine is suitable for densification and processing processes of composite materials.
The assembling area (the hangers) of the turbine outer ring on the engine is a static strength and vibration large stress area, so that a failure mode of layered destruction at the hangers is avoided, and the process forming performance is good. The turbine outer ring fiber prefabricated body is designed into an integral forming scheme, and is specifically divided into three areas for fiber laying and then combined forming, namely, an upper-layer arc-shaped part, a left-right C-shaped part and a lower-layer arc-shaped plate are adopted for laying. The large stress area at the assembly position of the turbine outer ring and the casing has fiber bearing capacity, and the interlayer strength is improved to the maximum extent through optimization of a laying scheme of fiber cloth or prepreg. And realizing the manufacture of the ceramic matrix composite turbine outer ring with high interlayer strength by subsequent densification and machining.
The fiber is the main bearing phase of the composite material, the structural form and the layering scheme of the fiber preform greatly influence the performance of the composite material member, and therefore the core content of the structural design of the composite material member is the layering scheme design of the fiber preform. The ceramic matrix composite has the characteristic of spatial anisotropy, and the interlayer strength (Z direction) level of the ceramic matrix composite is lower whether the ceramic matrix composite is a unidirectional tape or a two-dimensional paving prefabricated body; three-dimensional weaving improves interlaminar performance to some extent, but is still affected by its volume fraction content. In order to improve the strength and reliability of the ceramic matrix composite turbine outer ring in the Z direction, a split prefabricated body structure of pin combination connection is omitted, a fiber prefabricated body of the turbine outer ring is designed into an integrated structure and is divided into three regions, namely a pi-shaped piece on the upper surface layer, a left C-shaped piece, a right C-shaped piece and an arc plate piece on the lower surface layer, and as shown in figure 1, fibers are laid according to the regions and then are combined and shaped.
In some embodiments of the invention, the fiber preform of the turbine outer ring can be formed by laying unidirectional tape fiber prepreg, in order to ensure the strength performance of each direction of the space, the laying direction of the prepreg can be selected from one or more of 0 degree, 45 degrees and 90 degrees, and finally the ceramic matrix is densified by RMI; two-dimensional fiber warp and weft cloth (fiber cloth formed by cross weaving of fibers at 0 degree and 90 degrees) can also be adopted for laying and forming, and the fiber cloth is sewn among layers after the laying is finished according to the figure 1, so that the interlayer strength is improved, and the sewing mode is shown in the figure 2. Because the size of the outer ring lug of the turbine is thin, although the three-dimensional six-direction equal-weaving prefabricated body can improve the interlayer strength, the fiber introduction amount of the structure at the lug is less, the improvement degree of the interlayer strength is very limited, and in addition, the three-dimensional weaving process is complex and high in cost, so that the method is not suitable for the method.
In some embodiments of the invention, a layering proportioning design of the fiber preform is developed to improve the strength of the outer ring of the turbine in the Z direction to the maximum extent, and the fiber bearing effect of the left and right C-shaped parts and the pi-shaped part on the upper surface layer in the Z direction is fully exerted. The laying mode of the unidirectional tape fiber prepreg selects one laying direction of 0 degrees, 45 degrees and 90 degrees, the laying is carried out and laid along the loaded direction of the turbine outer ring, the laying quantity of each direction is designed through strength calculation and analysis, and the strength level of each direction of the space of the turbine outer ring part is ensured to meet the working condition requirement of an engine; adopt the preform of two-dimensional fiber cloth, its in-plane (xy direction) performance is unanimous, need not to develop and spreads the layer direction design, develops the fibre of different regions and spreads the layer quantity distribution, and the quantity proportion scope of pi-shaped piece and C-shaped piece is 1: 2-2: 1.
in some embodiments of the invention, after the fiber preform is prepared, a high-purity graphite mold is adopted for dimensional clamping, and densification processes such as CVI, PIP, RMI and the like with high adaptability are selected according to the structure type of the fiber preform for ceramic matrix densification, so that the outer ring blank of the ceramic matrix composite turbine is molded.
The turbine outer ring is in an inverted pi shape, the upper end of the turbine outer ring is assembled on the casing, the thickness of each section of the turbine outer ring is controlled within 3mm, the densification of composite materials is facilitated, and the density and the performance of parts are improved. In some embodiments of the invention, each part of the outer ring of the turbine is designed into a guide round and guide angle structure with excessive lubrication, which is convenient for processing composite materials and reduces stress concentration. As shown in fig. 3.
In some embodiments of the invention, in order to reduce the leakage of gas to the casing through the outer ring of the turbine, thereby affecting the efficiency of the engine, a sealing structure design of the outer ring of the turbine is developed. The lower bottom plate design of turbine outer loop is high, low overlap joint form, and every two turbine outer loops mutually support during the assembly promptly, form the structure of obturating of overlap joint form, prevent that the gas from outwards diffusing. As indicated by the arrows in fig. 4.
In some embodiments of the invention, in order to control the rotor and stator clearance (the clearance between the lower surface of the outer ring of the turbine and the tip of the rotor blade) and improve the efficiency of the turbine, the lower surface of the outer ring of the turbine is coated with an abradable seal coating matched with the ceramic composite material, and the abradable seal coating plays a role in preventing the tip of the blade from being abraded. As shown in fig. 5-7, in order to improve the bonding strength of the abradable coating, the bottom surface of the turbine outer ring is added with lattice grooves, recesses, surface honeycombs and other structural designs, and the grooves include structures such as straight lines or broken lines with different angles of 15 °, 30 °, 45 ° and the like; the depressions comprise cylindrical depressions and circular depressions, the diameter of the depressions is less than or equal to 1.5mm, and the hole depth of the depressions is 0.2-0.4 mm.
The above description is intended to be illustrative of the preferred embodiment of the present invention and should not be taken as limiting the invention, but rather, the intention is to cover all modifications, equivalents, and alternatives falling within the spirit and scope of the invention. The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, it is possible to make various improvements and modifications without departing from the technical principle of the present invention, and those improvements and modifications should be also considered as the protection scope of the present invention.
Claims (12)
1. A fiber preform is characterized by comprising a pi-shaped piece at an upper layer, a C-shaped piece matched with the pi-shaped piece and an arc-shaped piece arranged at a lower layer,
wherein the pi-shaped element is arranged in an inverted manner, and the C-shaped element is matched with the pi-shaped element left and right.
2. The fiber preform of claim 1, wherein the pi-shaped piece, the C-shaped piece, and the arc-shaped piece are made of unidirectional tape fiber prepreg.
3. A fibre preform according to claim 2, wherein the lay-up of unidirectional tape fibre prepregs comprises a lay-up angle selected from 0 °, ± 45 °, 90 °.
4. The fiber preform of claim 1, wherein the pi-shaped pieces, the C-shaped pieces, and the arc-shaped pieces are made of two-dimensional warp and weft cloth.
5. The fiber preform of claim 4, wherein the two-dimensional warp and weft fabrics are stitched together by fibers.
6. The fiber preform of claim 1, wherein the number ratio of the pi-shaped pieces to the C-shaped pieces is 1: 2-2: 1.
7. the fibrous preform of claim 1, wherein the fibers comprise alumina fibers or silicon carbide fibers.
8. A ceramic matrix composite turbine outer ring, wherein the turbine outer ring is a ceramic matrix composite turbine outer ring formed from the fiber preform of any of claims 1-7 by a CVI, PIP, RMI densification process.
9. The ceramic matrix composite turbine outer ring of claim 8, wherein said turbine outer ring is an inverted pi-shaped turbine outer ring, and the lower bottom plate of the turbine outer ring has a recess on one side and a protrusion on the other side for engaging with said recess.
10. The ceramic matrix composite turbine outer ring of claim 9, wherein a lower base plate surface of said turbine outer ring is provided with grooves and blind holes.
11. The outer ring of the ceramic matrix composite turbine of claim 10, wherein the blind holes are cylindrical or circular, have a diameter of 1.5mm or less and a hole depth of 0.2-0.5 mm.
12. The ceramic matrix composite turbine outer ring of claim 10, wherein said grooves are angled at an angle selected from the group consisting of 15 °, 30 ° and 45 ° to said bottom plate.
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| CN202010988304.9A CN112267917B (en) | 2020-09-18 | 2020-09-18 | Fiber preform and ceramic matrix composite turbine outer ring |
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| CN114014680A (en) * | 2021-11-19 | 2022-02-08 | 西北工业大学 | Ceramic matrix composite material turbine outer ring and preparation method thereof |
| CN114483207B (en) * | 2021-12-29 | 2024-03-08 | 西安鑫垚陶瓷复合材料股份有限公司 | Ceramic matrix composite turbine outer ring preform, shaping die and using method thereof |
| CN114850799B (en) * | 2022-05-23 | 2023-04-18 | 西安鑫垚陶瓷复合材料有限公司 | Ceramic matrix composite turbine outer ring machining tool and machining method |
| CN116384163B (en) * | 2023-06-05 | 2023-09-05 | 中国航发四川燃气涡轮研究院 | Design method of ceramic matrix composite complex component for aero-engine |
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