Thin kidney-shaped stator blade and closed blisk fan-shaped section of aero-engine compressor
By designing thin waisted static cotyledon blades and closed integrated blade fan sections, the fatigue and vibration problems of static cotyledon blades in high temperature and high pressure environments are solved, and the high stiffness and high temperature adaptability of static cotyledon blades are achieved, reducing processing costs and complexity.
Patent Information
- Application Number
- CN202510693081.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-05-27
- Publication Date
- 2025-07-18
AI Technical Summary
The static vanes of existing aircraft engine compressors are prone to fatigue cracks and vibrations in high temperature and high pressure environments, and the traditional damping structure increases component complexity and cost, and the application of materials is limited.
The tail edge of the thin waisted stator blade is concave, the bending area accounts for 15-30% of the leaf height, and the bending angle is 115-135°. It uses GH4251/GH4151 nickel-based high-temperature alloy, combined with the closed-type integrated blade fan section, to enhance the stiffness and strength of the stator blade.
Effectively reduce the aerodynamic and vibration loads of static cotyledon blades, improve fatigue life, reduce processing costs, adapt to high temperature environments above 750℃, and provide technical reserves of materials and structures.
Smart Images
Figure CN120332243A_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the technical field of the design of the stator components of aero-engine compressors, and specifically relates to a thin-waisted stator blade and a closed integral bladed disk sector of an aero-engine compressor. Background Art
[0002] The stator components of an aero-engine compressor include a casing and its stator blades. The stator blades at all levels are installed in the casing, located between two stages of rotor blades. The rotor blades compress air step by step through rotation, and the stator blades increase the air pressure through a diffusing effect.
[0003] The connection methods between the stator blades and the casing mainly include bolt fixation, welding, and sector track assembly. In existing mature multi-stage axial compressors of aero-engines, usually 6 - 30 stator blades are designed to be welded between the upper and lower arc-shaped flange plates to form a stator sector, and then multiple stator sectors are assembled into the casing through track assembly to form a complete ring structure.
[0004] The closed integral bladed disk sector as Figure 1 shown can maximize the integrity of the compressor flow path, the high consistency between blade profiles, and the minimum dispersion between blade profiles, enabling the compressor to obtain better aerodynamic performance and being widely used in high-pressure ratio compressors.
[0005] The stator components bear a relatively high temperature load during operation. Advanced compressors require the maximum temperature that the stator components can withstand to reach 700°C - 800°C. The existing materials for stator components are difficult to withstand such high temperatures. Therefore, it is necessary to reselect materials for the stator components.
[0006] In an environment where the aerodynamic load and temperature load of the compressor are relatively large, the stator blades will be greatly excited by the leading-edge airflow of the rear-stage rotor blades, easily generating fatigue cracks and even fractures. The application of new materials requires a blade configuration with low stress to be used for a long time.
[0007] Currently, most pairs of stator blades adopt damping vibration reduction. By adding damping structures to the upper and lower flange plates and their front and trailing edges, the vibration of the stator blades is reduced. However, the setting of the damping structure increases the complexity of the stator component structure, has a high manufacturing cost, poor safety, and is limited by the installation space, resulting in poor engineering applicability.
[0008] In addition, currently, to improve the performance of the compressor, the stator blades are designed as an arcuate structure, as Figure 2 shown, which is suitable for high-load compressors. However, while the arcuate stator blades bring a high pressure ratio, they also exacerbate the vibration of the stator blades at medium and high frequencies. Coupled with the high-temperature and high-pressure working environment, the fatigue life of the stator blades is greatly challenged, which also poses a great test to the application of new materials.
[0009] This application is proposed in view of the existence of the above-mentioned technical defects. Summary of the Invention
[0010] The purpose of this application is to provide a thin-waisted stator blade for an aero-engine compressor and a segment of a closed integrally bladed rotor (IBR) sector, so as to overcome or mitigate at least one aspect of the known technical defects.
[0011] The technical solution of this application is as follows:
[0012] A thin-waisted stator blade for an aero-engine compressor, the trailing edge of the stator blade is concave;
[0013] The position with the minimum chord length of the stator blade is at the blade midspan;
[0014] The chord length at the blade midspan of the stator blade is B1, and B1 = 60% - 85% of the maximum chord length of the stator blade;
[0015] The trailing edge root region of the stator blade has a small arc circumferential bend, the bending direction is the blade suction side direction, and the percentage of the bending region in the blade height is A1, and A1 = 15% - 30%.
[0016] According to at least one embodiment of this application, in the above-mentioned thin-waisted stator blade for an aero-engine compressor, the included angle between the trailing edge midspan region of the stator blade and the vertical direction is t2, and t2 = 5° - 15°.
[0017] According to at least one embodiment of this application, in the above-mentioned thin-waisted stator blade for an aero-engine compressor, the angle of the small arc circumferential bend in the trailing edge root region of the stator blade is t1, and t1 = 115° - 135°.
[0018] According to at least one embodiment of this application, in the above-mentioned thin-waisted stator blade for an aero-engine compressor, the stator blade is manufactured by machining with GH4251 / GH4151 nickel-based superalloy.
[0019] According to at least one embodiment of this application, in the above-mentioned thin-waisted stator blade for an aero-engine compressor, the stator blade is an arcuate blade.
[0020] A segment of a closed integrally bladed rotor (IBR) sector, including an upper rim plate and a lower rim plate in an arc shape, and a plurality of the above-mentioned thin-waisted stator blades for an aero-engine compressor;
[0021] Each stator blade is circumferentially supported between the upper rim plate and the lower rim plate and is integrally formed with the upper rim plate and the lower rim plate.
[0022] According to at least one embodiment of this application, in the above-mentioned segment of a closed integrally bladed rotor (IBR) sector, the leading edge of the lower rim plate has an inward mounting edge that can be connected by bolts. Brief Description of the Drawings
[0023] Figure 1 is a schematic diagram of a conventional closed - type integral bladed disk segment;
[0024] Figure 2 is a schematic diagram of a conventional bow - shaped stator vane;
[0025] Figure 3 is a schematic diagram of a thin - waist type stator vane of an aero - engine compressor provided by an embodiment of the present application;
[0026] Figure 4 is a comparative schematic diagram of the axial distance between the trailing edge of a conventional stator vane, the trailing edge of a thin - waist type stator vane and the leading edge of a subsequent - stage rotor vane provided by an embodiment of the present application;
[0027] Figure 5 is a schematic diagram of a closed - type integral bladed disk segment provided by an embodiment of the present application;
[0028] Figure 6 is a schematic diagram of the three - dimensional structure and the integral ring structure of a closed - type integral bladed disk segment provided by an embodiment of the present application.
[0029] For better illustration of this embodiment, some contents of the drawings are omitted, enlarged or reduced, which are only for exemplary illustration and should not be construed as a limitation to the present application. Detailed Embodiment
[0030] To make the technical solutions and their advantages of the present application clearer, the technical solutions of the present application will be further described clearly and completely below with reference to the drawings. It can be understood that the specific embodiments described herein are only part of the embodiments of the present application, which are only used to explain the present application rather than limit the present application. It should be noted that for the convenience of description, only the parts related to the present application are shown in the drawings, and other related parts can refer to the general design.
[0031] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of the present application should have the ordinary meanings understood by those of ordinary skill in the art to which the present application pertains. The "including" used in the description of the present application means that the concept appearing before this word covers the concepts listed after this word and their equivalents, without excluding other related concepts.
[0032] In addition, the terms indicating orientation used in the description of this application are only used to represent relative directions or positional relationships. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. It should also be noted that unless otherwise clearly specified and limited, terms such as "installation" and "connection" used in the description of this application should be understood in a broad sense. For example, connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium. Those skilled in the art can understand their specific meanings in this application according to specific circumstances.
[0033] Nickel-based superalloys such as GH4251 / GH4151 are new types of wrought superalloys that can withstand temperatures above 700 °C and can be used as materials for stator components to meet the high-temperature service requirements of 700 °C - 800 °C.
[0034] During the operation of a high-load compressor, the stator blades are mainly subjected to radial snap loads and axial aerodynamic loads. The blade configuration design can increase the radial stiffness and strength of the stator blades, reduce the axial aerodynamic load of the stator blades, and improve the fatigue life of the stator blades.
[0035] Based on the above, an embodiment of this application provides a compressor stator blade with a narrow waist shape for an aeroengine, as Figure 3 shown, the trailing edge is concave, forming a narrow waist structure that is wide at both ends and narrow in the middle.
[0036] Designing the trailing edge of the stator blade to have a narrowed waist can increase the axial distance between the trailing edge of the stator blade and the leading edge of the subsequent-stage rotor blade, lengthen the airflow diffusion channel, effectively reduce the airflow excitation force of the leading edge of the subsequent-stage rotor blade on the stator blade, reduce the aerodynamic load of the stator blade, thereby effectively reducing the vibration load of the stator blade. Moreover, this design is a subtractive design, which not only does not increase the complexity of the stator component structure, but also can reduce the consumables of the stator component, reduce the manufacturing cost of the stator component, and has high safety, is not restricted by the installation space, and has good engineering applicability.
[0037] The existing axial distance between the trailing edge of the stator blade and the leading edge of the subsequent-stage rotor blade is d1, and the axial distance between the trailing edge of the narrow-waist stator blade and the leading edge of the subsequent-stage rotor blade is d2. d2 is much larger than d1, and their comparison is shown in Figure 4.
[0038] The middle of the stator blade usually bears a large aerodynamic load. Designing the position with the minimum chord length of the stator blade to be in the middle of the blade, and the chord length in the middle is B1, B1 = 60% - 85% of the maximum chord length of the stator blade, can further reduce the local aerodynamic load of the stator blade.
[0039] The included angle between the middle region of the trailing edge of the stator blade and the vertical direction is t2, and t2 = 5° - 15°.
[0040] The air flow velocity in the root region of the stator vane is relatively fast, and it usually bears a large aerodynamic load. The small-arc circumferential bending in the root region of the trailing edge of the stator vane is designed, and the bending direction is the blade basin direction, which can further reduce the local aerodynamic load of the stator vane. The bending angle is t1, and t1 = 115° - 135°. The percentage of the area of the small-arc circumferential bending in the root of the trailing edge of the stator vane in the blade height is A1, and A1 = 15% - 30%.
[0041] The stacking axis of the stator vane is bow-shaped, that is, the configuration of the designed blade is a bow structure.
[0042] The stator vane is manufactured using the GH4251 / GH4151 nickel-based superalloy, that is, the selected material for the stator vane is the GH4251 / GH4151 nickel-based superalloy, which can withstand high temperatures of 700°C - 800°C and meet the temperature requirements for the operation of advanced compressors.
[0043] The thin-waisted stator vane of the aero-engine compressor disclosed in the above embodiment integrates the configuration, aerodynamics, and vibration reduction of the stator vane. In a high-temperature and high-pressure working environment, the trailing-edge thin-waisted stator vane can be used to reduce the aerodynamic and vibration loads during the use of the stator vane.
[0044] The thin-waisted stator vane of the aero-engine compressor disclosed in the above embodiment can effectively improve the "stiffness" and "strength" of the stator vane, reduce the vibration stress of the stator vane, improve the service life of the blade, lay a foundation for the application of high-temperature-resistant materials, and can solve the vibration and fatigue problems caused by "radial" and "axial" aerodynamic / alternating loads in a high-temperature environment, as well as solve the fatigue problems brought about by the long-term operation of the stator vane composed of the application of the GH4251 / GH4151 nickel-based superalloy in an environment of 750°C - 800°C. Compared with traditional materials, this "material selection + configuration" can increase the working temperature of the stator vane by about 100°C.
[0045] A closed integral bladed disk sector, as Figure 5 shown, includes an upper edge plate and a lower edge plate in an arc shape, and a plurality of thin-waisted stator vanes of the aero-engine compressor disclosed in the above embodiment.
[0046] The upper edge plate, the lower edge plate, and the stator vanes are made of the same material. Each stator vane is circumferentially supported between the upper edge plate and the lower edge plate and is integrally formed with the upper edge plate and the lower edge plate. It can be machined into a complete ring, or formed by 3D printing. After forming a complete ring, it can be divided to form a sector, or it can be used directly as a complete ring without cutting.
[0047] The leading edge of the lower edge plate can be further designed to have an inward mounting edge that can be connected by bolts, as Figure 6 shown.
[0048] The closed integral bladed disk fan segment disclosed in the above embodiments is designed based on the thin-waisted stator blade of the aero-engine compressor disclosed in the above embodiments, which can improve the strength and rigidity of the stator blade, has good fatigue resistance, can adapt to the working temperature of the compressor above 750 °C, and provides material and structural technology reserves for the design of the next-generation compressor.
[0049] So far, the technical solutions of the present application have been described in conjunction with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the protection scope of the present application.
Claims
1. A compressor stator blade with a slender waist shape for an aeroengine, characterized in that, The trailing edge of the stator vane is concave inwards; The position with the minimum chord length of the stator vane is at the mid-span of the vane; The chord length at the mid-span of the stator vane is B1, and B1 = 60% - 85% of the maximum chord length of the stator vane; In the root region of the trailing edge of the stator vane, there is a small-arc circumferential bend, and the bending direction is towards the suction side. The percentage of the bending region in the blade height is A1, and A1 = 15% - 30%.
2. The compressor stator vane with a narrow-waist shape for an aero-engine according to claim 1, wherein, The included angle between the mid-span region of the trailing edge of the stator vane and the vertical direction is t2, and t2 = 5° - 15°.
3. The compressor stator vane with a narrow-waist shape for an aero-engine according to claim 2, wherein, The angle of the small-arc circumferential bend in the root region of the trailing edge of the stator vane is t1, and t1 = 115° - 135°.
4. The compressor stator vane with a narrow-waist shape for an aero-engine according to claim 3, wherein, The stator vane is machined from GH4251 / GH4151 nickel-based superalloy.
5. The compressor stator vane with a narrow-waist shape for an aero-engine according to claim 4, wherein, The stator vane is an arc-shaped vane.
6. A closed integral bladed disk sector segment, characterized in that, It includes an upper edge plate and a lower edge plate in an arc shape, and a plurality of compressor stator vanes with a narrow-waist shape for an aero-engine as described in claim 1; Each stator vane is circumferentially supported between the upper edge plate and the lower edge plate and is integrally formed with the upper edge plate and the lower edge plate.
7. The segment of a closed integral bladed disk according to claim 6, wherein, The leading edge of the lower edge plate has an inward mounting edge that can be connected by bolts.