Lightweight high-strength aviation turbine blade structure

Abstract

The utility model provides a light-weight high-strength aviation turbine blade structure, belongs to the technical field of turbine blades, and aims to solve the problems that an existing blade of a hollow structure is poor in strength and not beneficial to long-time operation of the blade, and when the blade sucks high-temperature and high-pressure gas, the temperature of the blade can rise, and metal fatigue is prone to being generated. The blade comprises a connecting plate, a main body of the connecting plate is of a prismatic structure, two groups of connecting holes are formed in the surface of the connecting plate, and two through holes are formed in the surface of the connecting plate; the blade main body is of an arc-shaped structure, and the left end and the right end of the blade main body are of arc-shaped structures. According to the utility model, the guide pipe is fixedly arranged in the blade main body, the lower end of the guide pipe is respectively connected with the two heat dissipation grooves, the guide pipe can be made of copper materials, and after the guide pipe absorbs the heat in the cavity, the guide pipe can release the heat outwards through the heat dissipation grooves, so that the cooling effect on the blade main body can be achieved.

Description

Technical Field

[0001] This utility model belongs to the field of turbine blade technology, and more specifically, it relates to a lightweight, high-strength aero-turbine blade structure. Background Art

[0002] Currently, turbine blades are generally installed on the outside of the engine hub by riveting. When the blades rotate at high speed, they can draw high-temperature and high-pressure airflow into the combustor to maintain the engine's operation. However, the blades are prone to metal fatigue when working in the extreme environment of high temperature and high pressure for a long time, which is the most important cause of engine failure.

[0003] Based on the above, the current use of turbine blades still has the following two shortcomings:

[0004] First, in order to reduce the weight of the blades, the blades are made into a hollow structure. However, this method reduces the strength of the blades and is not conducive to the long-term operation of the blades.

[0005] Secondly, when the blades inhale high-temperature and high-pressure gas, their temperature rises, which can easily lead to metal fatigue. Currently, the heat dissipation effect of the blades is relatively poor. Utility Model Content

[0006] To address the aforementioned technical problems, this utility model provides a lightweight, high-strength aero-turbine blade structure. This solves the problems of poor strength in current hollow blade structures, which are not conducive to long-term blade operation, and the tendency for blades to experience metal fatigue due to increased temperature when inhaling high-temperature, high-pressure gases, while the current blades have relatively poor heat dissipation.

[0007] The purpose and effect of this utility model of lightweight high-strength aero-turbine blade structure are achieved by the following specific technical means: lightweight high-strength aero-turbine blade structure, including a connecting plate;

[0008] The main body of the connecting plate is a prismatic structure, and two sets of connecting holes are opened on the surface of the connecting plate. Two through holes are installed on the surface of the connecting plate.

[0009] The blade body has an arc-shaped structure, with arc-shaped structures at both ends and a cavity inside.

[0010] The insert plate has an arc-shaped main body, and two clamping plates are respectively installed on the front and rear end surfaces of the insert plate. The clamping plate body is also an arc-shaped main body.

[0011] The conduit has a U-shaped body, and its lower end is fixedly installed in a through hole on the surface of the connecting plate.

[0012] The guide plate has a long strip-shaped structure. A first sleeve is fixedly installed on one side of the left end of the guide plate, and a second sleeve is fixedly installed on one side of the right end of the guide plate.

[0013] Furthermore, the insert plate has two heat dissipation slots inside. The outlet end of the right heat dissipation slot is fixedly connected to the inlet end of the conduit, and the inlet end of the left heat dissipation slot is fixedly connected to the inlet end of the conduit.

[0014] Furthermore, a reinforcing rod is fixedly installed on the left side of the cavity inside the blade body, a first partition is fixedly installed in the middle of the cavity, and a second partition is installed on the right side of the cavity.

[0015] Furthermore, a set of first through holes are uniformly formed on the surface of the first partition, and two sets of second through holes are uniformly formed on the surface of the second partition.

[0016] Furthermore, two sets of clamping plates are installed at the front and rear ends of the insert plate, respectively. The main body of the clamping plate is an arc-shaped structure, and the main body of the connecting hole is a convex structure.

[0017] Furthermore, the first sleeve is fixedly installed on the outside of the reinforcing rod, the second sleeve is fixedly installed on the outside of the guide tube, and the guide plate is snapped into the first through hole on the surface of the first partition.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] In this invention, the surface of the connecting plate is provided with two sets of connecting holes. When the worker uses rivets to install the connecting plate on the surface of the wheel hub, the rivet part will be compressed into the inside of the connecting hole. Since the main body of the connecting hole is a convex structure, the stability of the connecting plate on the surface of the wheel hub can be improved.

[0020] In addition, the duct is fixedly installed inside the blade body, and the lower end of the duct is connected to two heat dissipation slots. The duct can be made of copper. After the duct absorbs the heat inside the cavity, it can release the heat outward through the heat dissipation slots, thereby cooling the blade body.

[0021] In addition, the left side of the blade body is relatively thin, and a reinforcing rod is installed at the left end of the internal cavity of the blade body to improve the strength of the blade body. The surface of the first partition plate has a first through hole, and the surface of the second partition plate has a second through hole. The first partition plate and the second partition plate can improve the strength of the blade body, and the setting of the first through hole and the second through hole can promote heat exchange inside the cavity. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the overall device structure of this utility model.

[0023] Figure 2This is a schematic diagram of the internal structure of the blade body of this utility model.

[0024] Figure 3 This is a schematic diagram of the blade structure from a top view.

[0025] Figure 4 This is a schematic diagram of the connection structure between the conduit and the second sleeve of this utility model.

[0026] Figure 5 This is an exploded structural diagram of the blade body and insert plate of this utility model.

[0027] Figure 6 This is a schematic diagram of the guide plate, the first sleeve, and the second sleeve of this utility model.

[0028] In the diagram, the correspondence between component names and drawing numbers is as follows:

[0029] 1. Connecting plate; 101. Connecting hole; 2. Blade body; 201. Cavity; 202. Reinforcing rod; 203. First partition plate; 2031. First through hole; 204. Second partition plate; 2041. Second through hole; 3. Insert plate; 301. Heat dissipation groove; 302. Clamping plate; 4. Guide tube; 5. Guide plate; 501. First sleeve; 502. Second sleeve. DETAILED DESCRIPTION

[0030] The embodiments of this utility model will be described in further detail below with reference to the accompanying drawings and examples.

[0031] Example 1:

[0032] As attached Figure 1 To the attached Figure 6 As shown:

[0033] This utility model provides a lightweight, high-strength aero-turbine blade structure, including a connecting plate 1;

[0034] The main body of the connecting plate 1 is a prismatic structure. Two sets of connecting holes 101 are opened on the surface of the connecting plate 1, and two through holes are installed on the surface of the connecting plate 1.

[0035] The blade body 2 has an arc-shaped structure, with arc-shaped structures at both ends, and a cavity 201 is provided inside the blade body 2.

[0036] Insert plate 3, the main body of insert plate 3 is an arc-shaped structure, and two clamping plates 302 are respectively installed on the front and rear end surfaces of insert plate 3. The main body of clamping plate 302 is an arc-shaped structure.

[0037] The conduit 4 has a U-shaped structure, and its lower end is fixedly installed in the through hole on the surface of the connecting plate 1.

[0038] Guide plate 5, the main body of guide plate 5 is a long strip structure, a first sleeve 501 is fixedly installed on the left side of guide plate 5, and a second sleeve 502 is fixedly installed on the right side of guide plate 5.

[0039] The insert plate 3 has two heat dissipation slots 301 inside. The outlet end of the right heat dissipation slot 301 is fixedly connected to the inlet end of the conduit 4, and the inlet end of the left heat dissipation slot 301 is fixedly connected to the inlet end of the conduit 4. After the conduit 4 absorbs the heat inside the cavity 201, it can release the heat to the outside.

[0040] A reinforcing rod 202 is fixedly installed on the left side of the cavity 201 inside the blade body 2, a first partition 203 is fixedly installed in the middle of the cavity 201, and a second partition 204 is installed on the right side of the cavity 201. The arrangement of the cavity 201 inside the blade body 2 reduces the weight of the blade body 2, and the first partition 203 and the second partition 204 provide support for the blade body 2, thereby improving the strength of the blade body 2.

[0041] The first partition 203 has a set of first through holes 2031 evenly opened on its surface, and the second partition 204 has two sets of second through holes 2041 evenly opened on its surface. In use, the arrangement of the first through holes 2031 and the second through holes 2041 can promote heat exchange inside the cavity 201.

[0042] Two sets of clamping plates 302 are installed at the front and rear ends of the insert plate 3, respectively. The main body of the clamping plate 302 is an arc-shaped structure, and the main body of the connecting hole 101 is a convex structure. The rivet part is compressed into the interior of the connecting hole 101. Since the main body of the connecting hole 101 is a convex structure, it can improve the stability of the connecting plate 1 on the hub surface. The lower end face of the connecting plate 1 is equipped with an arc-shaped insert plate 3, and two clamping plates 302 are installed at the front and rear ends of the insert plate 3, which can further enhance the stability of the blade body 2.

[0043] The first sleeve 501 is fixedly installed on the outside of the reinforcing rod 202, the second sleeve 502 is fixedly installed on the outside of the conduit 4, and the guide plate 5 is snapped into the first through hole 2031 on the surface of the first partition 203, which can promote heat exchange inside the cavity 201.

[0044] The specific usage and function of this embodiment are as follows:

[0045] In this invention, the surface of the connecting plate 1 has two sets of connecting holes 101. When the worker uses rivets to install the connecting plate 1 on the surface of the wheel hub, the rivet portion is compressed into the interior of the connecting holes 101. Since the main body of the connecting holes 101 has a convex structure, it can improve the stability of the connecting plate 1 on the surface of the wheel hub. The lower end face of the connecting plate 1 is equipped with an arc-shaped insert plate 3. Two clamping plates 302 are respectively installed at the front and rear ends of the insert plate 3, which can further enhance the stability of the blade body 2. When the blade body 2 is running, it will draw high-temperature and high-pressure airflow into the burner to maintain the operation of the engine. Therefore, the temperature of the blade body 2 will rise. The duct 4 is fixedly installed inside the blade body 2. The lower end of the duct 4 is connected to two diffusers respectively. The heat sink 301 is connected, and the conduit 4 can be made of copper. After the conduit 4 absorbs the heat inside the cavity 201, it can release the heat outward through the heat sink 301, thereby cooling the blade body 2. The left side of the blade body 2 is relatively thin, and a reinforcing rod 202 is installed at the left end of the cavity 201 inside the blade body 2 to improve the strength of the blade body 2. The surface of the first partition 203 has a first through hole 2031, and the surface of the second partition 204 has a second through hole 2041. The first partition 203 and the second partition 204 can improve the strength of the blade body 2, and the setting of the first through hole 2031 and the second through hole 2041 can promote heat exchange inside the cavity 201.

Claims

1. A lightweight, high-strength aerospace turbine blade structure, characterized in that: The system includes a connecting plate (1), the main body of which is a prismatic structure, and two sets of connecting holes (101) are opened on the surface of the connecting plate (1), and two through holes are installed on the surface of the connecting plate (1); a blade body (2), the blade body (2) is an arc-shaped structure, the left and right ends of the blade body (2) are arc-shaped structures, and a cavity (201) is opened inside the blade body (2); an insert plate (3), the main body of which is an arc-shaped structure, and two clamping plates (302) are respectively installed on the front and rear ends of the insert plate (3), and the main body of the clamping plate (302) is an arc-shaped structure; a guide tube (4), the main body of which is a U-shaped structure, and the lower end of the guide tube (4) is fixedly installed in the through hole on the surface of the connecting plate (1); and a guide plate (5), the main body of which is a long strip structure, and a first sleeve (501) is fixedly installed on one side of the left end of the guide plate (5), and a second sleeve (502) is fixedly installed on one side of the right end of the guide plate (5).

2. The lightweight, high-strength aerospace turbine blade structure as described in claim 1, characterized in that: The insert plate (3) has two heat dissipation slots (301) inside. The outlet end of the right heat dissipation slot (301) is fixedly connected to the inlet end of the conduit (4), and the inlet end of the left heat dissipation slot (301) is fixedly connected to the inlet end of the conduit (4).

3. The lightweight, high-strength aerospace turbine blade structure as described in claim 1, characterized in that: A reinforcing rod (202) is fixedly installed on the left side of the cavity (201) inside the blade body (2), a first partition (203) is fixedly installed in the middle of the cavity (201), and a second partition (204) is installed on the right side of the cavity (201).

4. The lightweight, high-strength aerospace turbine blade structure as described in claim 3, characterized in that: The surface of the first partition (203) is uniformly provided with a set of first through holes (2031), and the surface of the second partition (204) is uniformly provided with two sets of second through holes (2041).

5. The lightweight, high-strength aerospace turbine blade structure as described in claim 1, characterized in that: The front and rear ends of the insert plate (3) are respectively equipped with two sets of card plates (302). The main body of the card plate (302) is an arc-shaped structure, and the main body of the connecting hole (101) is a convex structure.

6. The lightweight, high-strength aerospace turbine blade structure as described in claim 1, characterized in that: The first sleeve (501) is fixedly installed on the outside of the reinforcing rod (202), the second sleeve (502) is fixedly installed on the outside of the guide tube (4), and the guide plate (5) is snapped into the first through hole (2031) on the surface of the first partition (203).

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