Fan blade flow guide structure, fan and aero-engine

Abstract

The fan blade flow guide structure is used for guiding flow of fan blades, the rear edge of each fan blade is provided with a tangent plane, the rear edge side of each fan blade is close to an annular component, the flow guide structure comprises a flow guide plate arranged on the annular component, and the appearance of the flow guide plate is in smooth transition with the blade profile of the rear edge of each fan blade. The blade appearance lacking of the tangent plane of the rear edge of the fan blade is supplemented, airflow separation of the rear edge of the fan blade is achieved, the wake of the blade is guided, and the aerodynamic performance is optimized. The utility model further provides a fan and an aero-engine.

Description

Technical Field

[0001] The utility model relates to the field of engine blades, in particular to the field of fan blade flow guide structures. Background Art

[0002] Modern turbofan aircraft engines are developing towards high bypass ratio, high thrust, low fuel consumption, low noise, high safety and high reliability. Fan blades are one of the most important parts of the compressor, which directly affects the aerodynamic performance, working reliability, quality and cost of the compressor. In order to facilitate processing, the trailing edge of the fan blade is generally cut directly from the blank, and the blade shape lacks a smooth transition. When high-speed airflow passes through, airflow separation may occur, thereby affecting the supercharging effect of subsequent components such as the supercharging stage. How to reduce airflow separation, optimize the aerodynamic performance of fan blades, and improve compressor efficiency has become a technical problem that needs to be solved urgently. Utility Model Content

[0003] One purpose of the utility model is to provide a fan blade guide structure, which can reduce the airflow separation at the trailing edge of the blade and improve the working efficiency of the compressor.

[0004] To achieve the above-mentioned purpose, a fan blade guide structure is used to guide fan blades, wherein the trailing edge of the fan blade has a section, and the trailing edge of the fan blade is close to an annular component. The guide structure includes a guide plate, which is arranged on the annular component, and the shape of the guide plate smoothly transitions with the blade shape of the trailing edge of the fan blade.

[0005] In one or more embodiments, the two airfoil profiles of the guide plate smoothly transition with the blade back profile and the blade basin profile on the trailing edge side of the fan blade.

[0006] In one or more embodiments, the annular component is a sealing ring or a stator inner ring of a compressor.

[0007] In one or more embodiments, the guide plate is integrally formed with the annular component.

[0008] In one or more embodiments, the guide plate is arranged parallel to the engine axis.

[0009] In one or more embodiments, the two airfoil surfaces of the guide plate are consistent with the inclination direction of the trailing edge of the fan blade.

[0010] In one or more embodiments, the guide plates correspond to the fan blades.

[0011] In one or more embodiments, the height of the guide plate ranges from 10% to 70% of the height of the fan blade.

[0012] Another object of the utility model is to provide a fan adopting the above-mentioned fan blade guide structure.

[0013] Another object of the utility model is to provide an aircraft engine, which includes a fan, a compressor, a combustion chamber, and a turbine, wherein the fan adopts the above-mentioned fan with a fan blade guide structure.

[0014] The above-mentioned fan blade guide structure installs a guide plate close to the trailing edge of the fan blade to make the blade profile smoother, make up for the missing blade shape of the fan blade trailing edge section, solve the airflow separation at the trailing edge of the fan blade, guide the blade wake, and meet the optimization of aerodynamic performance to achieve the effect of reducing airflow separation and thus improving compressor efficiency, which meets the urgent need to improve compressor efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which:

[0016] Figure 1 is a schematic diagram of one embodiment of a fan blade;

[0017] Figure 2 is along Figure 1 Cross-section view in the AA direction;

[0018] Figure 3 yes Figure 2 The enlarged view of point B in the middle;

[0019] Figure 4 is a schematic diagram of the leading and trailing edges of a fan blade;

[0020] Figure 5 It is a schematic diagram of the positions of the fan blades and the annular components on the trailing edge side;

[0021] Figure 6 is a front view of an embodiment of a sealing ring with a guide plate;

[0022] Figure 7 It is a right side view of an embodiment of a sealing ring with a guide plate;

[0023] Figure 8 It is a schematic diagram of the matching position of the sealing ring with guide plate and the fan blade;

[0024] Fig. 9 is along Figure 8 Cross-sectional view in the mid-CC direction;

[0025] Fig.10 yes Fig. 9 The enlarged view of point D in the middle;

[0026] Fig.11 It is a schematic diagram of the structure with smooth transition between the guide plate and the trailing edge of the fan blade.

[0027] Symbols and Markings

[0028] 1 Fan Blade

[0029] 11 Leaf Back

[0030] 12 Leaf Basin

[0031] 13 Section

[0032] 2 Drum sealing ring

[0033] 3 Zero-stage stator inner ring

[0034] 4 Deflector

[0035] 41 Wing DETAILED DESCRIPTION

[0036] The present invention is further described below in conjunction with specific embodiments and drawings. More details are elaborated in the following description to facilitate a full understanding of the present invention. However, the present invention can obviously be implemented in a variety of other ways different from the description. Those skilled in the art can make similar generalizations and deductions based on actual application situations without violating the connotation of the present invention. Therefore, the protection scope of the present invention should not be limited by the content of this specific embodiment.

[0037] It should be noted that these and other subsequent drawings are only examples and are not drawn in proportion, and should not be used as a limitation on the actual scope of protection required by the present utility model.

[0038] like Figure 1-Figure 4 The fan blade 1 shown is provided with a leading edge a, a trailing edge b, a blade back 11 and a blade basin 12. In the common processing method of the fan blade, the trailing edge b is mostly a cut surface 13, that is, a vertical plane, such as Figure 3 As shown, there is a defect at the trailing edge of the entire blade profile, lacking a smooth transition.

[0039] like Figure 5 As shown, in the compressor structure, the trailing edge of the fan blade 1 is adjacent to the annular component, which is the sealing ring 2 and / or the compressor stator inner ring 3. In order to guide the fan blade wake and improve the compressor efficiency, a fan blade guide device can be added to the annular component.

[0040] The fan blade guide structure disclosed in the present invention refers to Figures 6 to 9 As shown, the blade guide structure includes a guide plate 4, which is arranged on an annular component close to the trailing edge side of the fan blade, that is, the trailing edge flow channel area of ​​the fan blade. Figures 6 to 9 In the illustrated embodiment, the guide plate 4 is arranged on the sealing ring 2 .

[0041] The rear edge of the fan blade has a cut surface 13, so that the tail of the fan blade 1 appears incomplete, and the shape of the guide plate 4 is set to smoothly transition with the blade shape of the rear edge b of the fan blade.

[0042] Specifically, if Fig.11 As shown, the contour lines of the two wing surfaces 41 of the guide plate 4 smoothly transition with the contour lines of the blade back 11 and the blade basin 12 near the trailing edge of the fan blade, and are consistent with the fan blade. The two wing surfaces 41 of the guide plate 4 refer to the two side surfaces of the guide plate 4 in the circumferential direction.

[0043] The setting of the guide plate 4 can be understood as filling in the missing blade shape due to the section of the trailing edge of the fan blade, so that the guide plate and the fan blade form a complete smooth blade shape. The airflow passes through the guide structure at the trailing edge of the fan blade, reducing airflow separation and effectively improving the compressor efficiency.

[0044] Preferably, the guide plates 4 correspond to the fan blades 1 one by one.

[0045] Considering that the fan blade root is less deformed when the engine is running and the installation state is more stable, the guide plate 4 is installed behind the blade root to guide the fan blade wake, which can better play the guiding role. The height range of the guide plate is preferably 10% to 70% of the height of the fan blade 1.

[0046] In some embodiments, the guide plate can be integrally formed with the sealing ring or the stator inner ring, such as Figure 6 The guide drum sealing ring structure shown adopts an integral molding method, and adds a fan blade trailing edge guide plate 4 on the basis of a traditional drum sealing ring to form a whole, omitting subsequent cumbersome assembly steps and simplifying the assembly process.

[0047] Continue to refer to Fig. 9 and Fig.10 As shown in the schematic diagram of the guide structure, the guide plate 4 can be arranged parallel to the engine axis, such as Fig.10 As shown, the two wing surfaces 41 of the guide plate 4 can also be set to be consistent with the inclination direction of the trailing edge of the fan blade, as shown in FIG. Fig.11 shown.

[0048] The above-mentioned guide structure makes the blade profile smoother by installing a guide plate close to the trailing edge of the blade, solves the airflow separation at the trailing edge of the fan blade, guides the blade wake, and meets the optimization of aerodynamic performance to reduce airflow separation and thus improve compressor efficiency, which is an urgent need to improve compressor efficiency.

[0049] Combined with the above introduction to the fan blade guide structure, it can be understood that a fan adopts the above fan blade guide structure and an aircraft engine including the fan, the blade guide structure is arranged on the sealing ring or the stator inner ring of the compressor, and effectively guides the air flow, so that the fan and aircraft engine provided with the above fan blade guide structure have better airflow efficiency.

[0050] At the same time, the present application uses specific words to describe the embodiments of the present application. For example, "one embodiment", "an embodiment", and / or "some embodiments" refer to a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or more in different positions in this specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0051] Although the utility model is disclosed as above with preferred embodiments, it is not intended to limit the utility model. Any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the utility model. Therefore, any modification, equivalent change and modification made to the above embodiments based on the technical essence of the utility model without departing from the content of the technical solution of the utility model shall fall within the protection scope defined by the claims of the utility model.

Claims

1. A fan blade guide structure, used for guiding fan blades, wherein the trailing edge of the fan blade has a cut surface, and the trailing edge of the fan blade is close to an annular component, characterized in that: The flow guide structure comprises a flow guide plate, which is arranged on the annular component, and the shape of the flow guide plate is smoothly transitioned with the blade shape of the trailing edge of the fan blade.

2. The fan blade guide structure according to claim 1, characterized in that: The two wing surface profiles of the guide plate smoothly transition with the blade back profile and the blade basin profile of the fan blade close to the trailing edge.

3. The fan blade guide structure according to claim 1, characterized in that: The annular component is a sealing ring or a stator inner ring of a compressor.

4. The fan blade guide structure according to claim 3, characterized in that: The guide plate is integrally formed with the annular component.

5. The fan blade guide structure according to claim 1, characterized in that: The guide plate is arranged parallel to the engine axis.

6. The fan blade flow guide structure according to claim 1, characterized in that: The two wing surfaces of the guide plate are in the same inclination direction as the trailing edge of the fan blade.

7. The fan blade flow guide structure according to claim 1, characterized in that: The guide plates correspond to the fan blades one by one.

8. The fan blade guide structure according to claim 1, characterized in that: The height of the guide plate ranges from 10% to 70% of the height of the fan blades.

9. A fan, characterized in that The fan adopts the fan blade guide structure as described in any one of claims 1-8.

10. An aircraft engine, comprising a fan, a compressor, a combustion chamber, and a turbine, characterized in that: The fan is the fan according to claim 9.

Images