A compressor composite blade root load bearing structure

Abstract

The utility model relates to a compressor composite blade blade root bearing structure, including the blade root core and blade root outer layer of composite material, the blade root core is equipped with first boss, the blade root outer layer is with the shape and is attached to the first boss surface, the end face of first boss near blade root end part is processed into first taper surface structure, the blade root outer layer completely covers and corresponds and is attached on first taper surface structure, another end face of first boss is processed into second taper surface structure, the blade root outer layer corresponds and is attached on second taper surface structure. The utility model will be the end face of first boss of blade root core and be processed into first taper surface structure, and the blade root outer layer completely covers and corresponds and is attached on first taper surface structure to solve the problem between blade root core and blade root outer layer interlayer separation under the verification of tensile test, has strengthened the tensile property of blade root.

Description

Technical Field

[0001] This utility model relates to a root load-bearing structure for a compressor composite blade, belonging to the field of compressor blade technology. Background Technology

[0002] The compressor blades operate at a high speed during rotation. Under high-speed operation and due to the weight of the blades themselves, the blades generate a large centrifugal force during rotation. The carbon beams of the blades bear almost all of the centrifugal force and bending moment.

[0003] Traditional composite propeller blades use a classic clasp beam, such as... Figure 4 As shown, the blade's carbon beam portion consists of a skin and a main load-bearing carbon beam structure of a certain thickness and width added inside the skin. A foam core layer is sandwiched between the carbon beams. However, during analysis and calculations, it was found that when using this type of existing carbon beam, regardless of how much the carbon beam thickness is increased, the blade's design stiffness is difficult to meet the required standards. Increasing stiffness means reducing the amount of blade deformation under load. Utility Model Content

[0004] The purpose of this invention is to provide a carbon beam for the main load-bearing component of composite blades, which solves the problem of insufficient stiffness of existing carbon beams for the main load-bearing component of composite blades under limited weight requirements.

[0005] The present invention adopts the following technical solution:

[0006] A compressor composite blade root load-bearing structure includes a composite blade root core 100 and a blade root outer layer 200. The blade root core 100 is provided with a first boss 101, and the blade root outer layer 200 conformally adheres to the surface of the first boss 101. The end face of the first boss 101 near the blade root end is processed into a first conical structure 102, and the blade root outer layer 200 is completely covered and correspondingly adhered to the first conical structure 102. The other end face of the first boss 101 is processed into a second conical structure 103, and the blade root outer layer 200 is correspondingly adhered to the second conical structure 103.

[0007] Preferably, the blade root is located at the rear end of the blade and serves as the main load-bearing structure. It is installed inside the turntable and is mainly subjected to centrifugal force during operation. The first boss 101 serves as the main load-bearing part. The blade root core 100 is shaped by a hot autoclave process after being laid with a mold. The outer layer 200 of the blade root is shaped by a hot autoclave process after being laid on the surface of the blade root core 100. The angle of the second conical structure 103 is set between 40 and 50 degrees.

[0008] Furthermore, the angle of the second conical structure 103 is set at 45 degrees.

[0009] Preferably, a second boss 201 is machined on the outer layer 200 of the leaf root.

[0010] Furthermore, both end faces of the second boss 201 are machined into tapered surfaces.

[0011] Furthermore, the second boss 201 is supported by multiple pads inside.

[0012] The beneficial effects of this utility model are as follows: the end face of the first protrusion of the blade root core is processed into a first conical surface structure, and the outer layer of the blade root is completely covered and attached to the first conical surface structure. Thus, the problem of interlayer separation between the blade root core and the outer layer of the blade root is solved under the verification of tensile test, the tensile performance of the blade root is enhanced, and the tensile load is increased from 160 tons to 200 tons. Attached Figure Description

[0013] Figure 1 This is a three-dimensional schematic diagram of the root load-bearing structure of the composite material blade of the compressor according to this utility model.

[0014] Figure 2 This is an axial cross-sectional view of the blade root load-bearing structure of the compressor composite material blade of this utility model.

[0015] Figure 3 A cross-sectional photograph of the axial section after a tensile test on the actual object used for comparison with this utility model (the outer edge of the rear end of the outer layer of the blade root is flush with the blade root core, as shown in part A' in the figure).

[0016] Figure 4 This is a force analysis diagram of the second conical surface structure of the blade root bearing structure of the compressor composite material blade of this utility model.

[0017] In the figure, 100 is the leaf root core, 101 is the first boss, 102 is the first conical surface structure, 103 is the second conical surface structure, 200 is the outer layer of the leaf root, 201 is the second boss, 202 is the third conical surface structure, and 203 is the fourth conical surface structure. Detailed Implementation

[0018] The present invention will be further described below with reference to the accompanying drawings and specific embodiments. The technical solutions in the embodiments of the present invention will be clearly and completely described. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are also described.

[0019] Example 1:

[0020] See Figure 1-2A compressor composite blade root load-bearing structure includes a composite blade root core 100 and a blade root outer layer 200. The blade root core 100 is provided with a first boss 101. The blade root outer layer 200 conformally fits onto the surface of the first boss 101. The end face of the first boss 101 near the blade root end is processed into a first conical structure 102. The blade root outer layer 200 completely covers and is correspondingly fitted onto the first conical structure 102. The other end face of the first boss 101 is processed into a second conical structure 103. The blade root outer layer 200 is correspondingly fitted onto the second conical structure 103.

[0021] In this embodiment, see Figure 2 The blade root is located at the rear end of the blade and serves as the main load-bearing structure. It is installed inside the turntable and is mainly subjected to centrifugal force during operation. The first boss 101 serves as the main load-bearing part. The blade root core 100 is shaped by a hot autoclave process after being laid with a mold. The outer layer 200 of the blade root is shaped by a hot autoclave process after being laid on the surface of the blade root core 100. The angle of the second conical structure 103 is set between 40 and 50 degrees.

[0022] See Figure 4 Symbol explanation:

[0023] Freaction: the supporting reaction force of centrifugal force;

[0024] F-pressure: The pressure exerted by centrifugal force on the conical surface;

[0025] Fcomponent: The component of centrifugal force generated along the conical surface;

[0026] α: Angle of the conical surface.

[0027] The angles of the conical surface are listed and compared using three values: 40 degrees, 45 degrees, and 50 degrees.

[0028]

[0029]

[0030] When α is 40 degrees, F 分 ≥F 压 ;

[0031] When α is 45 degrees, F 分 =F 压 ;

[0032] When α is 50 degrees, F 分 ≤F 压 .

[0033] In F 分 =F 压At this time, the forces generated by these two component forces that are parallel to the direction of the centrifugal force and perpendicular to the direction of the centrifugal force are the same, and the left and right component forces cancel each other out, forming an internal force (as shown by the red arrow in the diagram above). If F 分 and F 压 Since they are not the same, they cannot cancel each other out, and the additional force will place a large load on the product and other mating parts. After analysis, the optimal value of α was finally selected as 45°.

[0034] Therefore, the angle of the second conical structure 103 is preferably 45°.

[0035] It should be noted that, see Figure 2 Part A in the middle (and Figure 3 (In contrast to part A' in the figure), this embodiment designs a tapered surface at the rear end of the first protrusion 101 of the blade root and completely covers the outer layer 200 of the blade root with it. This increases the axial force-bearing surface of the blade root when it is under stress, avoids the problem of circumferential delamination from the first protrusion 101, and improves the reliability of the blade root during operation.

[0036] In this embodiment, see Figure 2 The outer layer 200 of the leaf root is provided with a second protrusion 201.

[0037] In this embodiment, see Figure 2 Both ends of the second boss 201 are machined into tapered surfaces.

[0038] In this embodiment, see continue to see Figure 2 The second boss 201 is supported by multiple pads inside.

[0039] In this embodiment, the end face of the first boss of the blade root core is processed into a first conical surface structure, and the outer layer of the blade root is completely covered and attached to the first conical surface structure. Thus, the problem of interlayer separation between the blade root core and the outer layer of the blade root is solved under the verification of tensile test, and the tensile performance of the blade root is enhanced, and the tensile load is increased from 160 tons to 200 tons.

[0040] Example 2 (Comparative Example):

[0041] The accompanying drawings for this embodiment are as follows: Figure 3 This is provided as a comparative example only and does not imply that the comparative example is prior art. It is merely a comparison conducted by the applicant during the research and development process. See [link to relevant documentation]. Figure 3 In this embodiment, at part A', the left end of the outer layer of the leaf root is flush with the leaf root core and does not completely cover the leaf root core. The leaf root core and the outer layer of the leaf root exhibit a separation phenomenon between corresponding surface layers at the first protrusion, and the tensile load is only 160 tons.

[0042] This embodiment is mainly used to compare with Embodiment 1 and prove that the solution in Embodiment 1 is superior.

[0043] It should be noted that the above embodiments are preferred embodiments of the present utility model. Those skilled in the art can make various changes or improvements on this basis. Without departing from the overall concept of the present utility model, these changes or improvements should all fall within the scope of protection claimed by the present utility model.

Claims

1. A compressor composite blade root load-bearing structure, characterized in that: It includes a composite material blade root core (100) and a blade root outer layer (200). The leaf root core (100) is provided with a first protrusion (101), and the leaf root outer layer (200) conformally fits to the surface of the first protrusion (101). The end face of the first boss (101) near the end of the leaf root is processed into a first conical structure (102), and the outer layer (200) of the leaf root is completely covered and attached to the first conical structure (102); The other end face of the first boss (101) is processed into a second conical structure (103), and the outer layer (200) of the leaf root is correspondingly attached to the second conical structure (103).

2. The compressor composite blade root load-bearing structure as described in claim 1, characterized in that: The blade root is located at the rear end of the blade and serves as the main load-bearing structure. It is installed inside the turntable and is mainly subjected to centrifugal force during operation. The first boss (101) serves as the main load-bearing part. The blade root core (100) is laid by a mold and then shaped by a hot press process. The outer layer (200) of the blade root is laid on the surface of the blade root core (100) and then shaped by a hot press process. The angle of the second conical structure (103) is set between 40 and 50 degrees.

3. The compressor composite blade root load-bearing structure as described in claim 2, characterized in that: The angle of the second conical structure (103) is set at 45 degrees.

4. The compressor composite blade root load-bearing structure as described in claim 1, characterized in that: A second boss (201) is machined on the outer layer (200) of the leaf root.

5. The compressor composite blade root load-bearing structure as described in claim 4, characterized in that: Both ends of the second boss (201) are machined into tapered surfaces.

6. The compressor composite blade root load-bearing structure as described in claim 5, characterized in that: The second boss (201) is supported by multiple pads inside.

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