Inlet flow guide support plate and turbine component
The redesign of inlet guide vanes with a tapered shape addresses flow separation issues, enhancing aerodynamic performance by maintaining higher flow velocities and reducing drag.
Patent Information
- Application Number
- CN202422259969.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-09-13
- Publication Date
- 2025-07-15
- Estimated Expiration
- 2034-09-13
AI Technical Summary
The flow guide plates of existing turbine components are prone to flow separation during the airflow flow, resulting in a degradation of aerodynamic performance, especially at the outer flow channel, which is high risk of separation, affecting the normal operation of the test turbine.
An inlet guide support plate is designed, with the top surface inclined toward the tail edge, causing it to shrink inward, reduce the degree of expansion of the outer flow channel, and connect through arc transitions to suppress flow separation. The improved support plate thickness gradually increases from the leading edge to the maximum and then gradually shrinks, forming a water droplet-like cross-section.
It effectively suppresses the flow separation at the outer flow channel, improves the aerodynamic performance of the flow guide bracket, avoids adverse effects on the test turbine, and improves the advantages of the aerodynamic shape.
Smart Images
Figure CN223104670U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of aero-engines, in particular to an inlet guide vane and a turbine component. Background Art
[0002] The turbine is one of the three major components of an aero-engine, located behind the combustion chamber. Its main function is to convert most of the energy of the high-temperature and high-pressure gas flowing out of the combustion chamber into mechanical work, driving the compressor, fan, propeller, rotor, and accessory drive system, etc. The turbine is composed of a non-rotating stator part and a rotating rotor part. The stator part mainly includes components such as turbine guide vanes and turbine casings, and the rotor part mainly includes turbine blades, turbine disks, and turbine shafts.
[0003] Currently, common tests for turbine components include turbine performance tests, turbine guide vane flow function tests, etc. The test piece of the turbine component generally includes an inlet section, a test section, and an outlet section. The inlet section connects the test bench and the test section, guiding the gas provided by the test bench to the turbine component in the test section. The designed guide vane in the inlet section can establish a transfer flow path between the test bench and the test turbine, provide a fulcrum for the rotor of the test turbine, and provide a passage for the gas supply pipeline of the test turbine.
[0004] However, to achieve the guiding effect, the guide vane generally has the "water droplet shape" of an aircraft wing. For the flow path between two adjacent guide vanes, the flow path width first contracts and then expands. The corresponding surface pressure of the guide vane first decreases and then increases. After the air flow passes through the maximum thickness position of the guide vane, due to the decrease in the curvature of the guide vane, the air flow velocity decreases and the kinetic energy weakens. At the same time, due to the start of the expansion of the flow path, the air flow pressure increases, and the resistance faced by the air flow increases. When the kinetic energy of the air flow itself is not sufficient to resist the large flow resistance, the air flow will separate from the surface of the guide vane and then a backflow will occur. Since the radius of the annular flow path gradually increases from the inside to the outside and the circumferential length of the annular flow path increases, the degree of expansion near the outer flow path will be greater, so the risk of air flow separation at the outer flow path position is higher. The air flow separates at the position of the guide vane near the outer flow path. And large flow separation on the flow path surface of the guide vane will have an adverse impact on the test turbine. Summary of the Utility Model
[0005] The purpose of the utility model is to provide an inlet guide vane and a turbine component, which can improve the aerodynamic performance of the inlet guide vane.
[0006] One aspect of the present utility model provides an inlet guide vane, and the inlet guide vane includes an opposite vane tip and a vane root; the inlet guide vane further includes a top surface disposed at the vane tip; the top surface is used to connect to an external casing, and the vane root is used to connect to an internal casing; at least a part of the top surface extends obliquely towards the vane root along the chord length direction to the trailing edge of the inlet guide vane.
[0007] In one embodiment, the thickness of the inlet guide vane gradually increases from the leading edge and gradually decreases to the maximum thickness.
[0008] In one embodiment, the top surface includes an un-inclined portion extending from the leading edge of the inlet guide vane to the maximum thickness and an inclined portion extending from the maximum thickness to the trailing edge; the inclined portion extends obliquely towards the vane root along the chord length direction at the maximum thickness to the trailing edge.
[0009] In one embodiment, the included angle between the inclined portion and the un-inclined portion of the top surface is 15° to 30°.
[0010] In one embodiment, the inclined portion and the un-inclined portion are connected by an arc transition.
[0011] In one embodiment, the radius of the arc at the arc transition connection is 20 to 90 mm.
[0012] Another aspect of the present utility model provides a turbine component, including an external casing and an internal casing, and the turbine component further includes an inlet guide vane as described in any one of the above embodiments; the top surface of the inlet guide vane is connected to the external casing, and the vane root of the inlet guide vane is connected to the internal casing.
[0013] In one embodiment, there are a plurality of the inlet guide vanes, and the plurality of inlet guide vanes are arranged at intervals along the outer circumference of the internal casing; a flow passage is formed between two adjacent inlet guide vanes, the external casing, and the internal casing.
[0014] In one embodiment, the inlet guide vane is welded to the external casing and the internal casing.
[0015] In one embodiment, the inlet guide vane, the external casing, and the internal casing are integrally formed.
[0016] The top surface of the inlet guide vane of the present utility model is inclined towards the trailing edge, causing the top surface to contract inward. Compared with the inlet guide vane with a flat top surface before improvement, the present utility model can reduce the expansion degree of the external flow passage, effectively suppress the flow separation at the external flow passage, avoid large flow separation on the flow passage surface of the guide vane and have an adverse impact on the tested turbine, make the profile of the guide vane have an excellent aerodynamic shape, and improve the aerodynamic performance of the guide vane. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] The above and other features, properties and advantages of the present utility model will become more apparent through the following description with reference to the drawings and embodiments, where:
[0018] Figure 1 is a schematic diagram of a turbine test piece;
[0019] Figure 2 is a cross-sectional schematic diagram of an inlet guide vane;
[0020] Figure 3 is Figure 2 a schematic diagram of the surface pressure distribution of the inlet guide vane shown;
[0021] Figure 4 is a schematic diagram of the inlet guide vane before improvement;
[0022] Figure 5 is Figure 4 a schematic diagram of the surface streamline of the inlet guide vane before improvement shown;
[0023] Figure 6 is a schematic diagram of an embodiment of the inlet guide vane according to the present utility model;
[0024] Figure 7 is Figure 6 a side view of the inlet guide vane shown;
[0025] Figure 8 is Figure 6 a schematic diagram of the surface streamline of the inlet guide vane shown;
[0026] Figure 9 is Figure 6 a schematic diagram of the angle of the inlet guide vane shown;
[0027] Figure 10 is Figure 6 a schematic diagram of the formation of the inlet guide vane shown;
[0028] Figure 11 is Figure 6 a schematic diagram of the connection between the inlet guide vane and the internal casing shown;
[0029] Figure 12 isFigure 6 Schematic diagram showing the connection of the inlet guide vane to the inner casing and the outer casing. Detailed implementation mode
[0030] Now, reference will be made in detail to the embodiments of the present invention, one or more examples of which are shown in the accompanying drawings. Each example is provided to explain the present invention, not to limit the present invention. In fact, it will be obvious to those skilled in the art that various modifications and variations can be made to the present invention without departing from the scope or spirit of the present invention. For example, features shown or described as part of one embodiment can be used with another embodiment to yield yet another embodiment. Accordingly, the present invention is intended to cover such modifications and variations that fall within the scope of the appended claims and their equivalents.
[0031] As used herein, the term "axial" is the central axis of the inner casing or the direction parallel to the central axis of the inner casing, and the term "circumferential" is the direction around the "axial". The terms "upstream" and "downstream" refer to the relative directions with respect to the airflow in the flow path. For example, "upstream" refers to the direction from which the airflow flows, and "downstream" refers to the direction towards which the airflow flows.
[0032] The turbine is one of the three major components of an aeroengine and is located behind the combustion chamber. Its main function is to convert most of the energy of the high-temperature and high-pressure gas flowing out of the combustion chamber into mechanical work, driving the compressor, fan, propeller, rotor, and accessory drive system, etc. The turbine is composed of a non-rotating stator part and a rotating rotor part. The stator part mainly includes components such as turbine guide vanes and turbine casings, and the rotor part mainly includes turbine blades, turbine disks, and turbine shafts.
[0033] Experimental research plays a very important role and status in the development of turbines for aeroengines and gas turbines. Experimental research can experimentally verify the results of theoretical research and at the same time provide a reliable basis for correcting theoretical methods. Currently, common turbine component tests include turbine performance tests, turbine guide vane flow function tests, etc.
[0034] Figure 1 The structure of a turbine component test piece is shown. The turbine component test piece generally includes an inlet section, a test section, and an outlet section. The inlet section connects the test bench to the test section and guides the gas provided by the test bench to the test turbine 4 in the test section. The main functions to be achieved by the inlet section include:
[0035] (1) Establish a transfer flow path between the test bench and the test turbine 4. Since there must be a certain difference between the size interfaces of the test bench and the test turbine, in order to enable the gas to flow smoothly from the test bench to the test turbine 4, it is necessary to establish a transfer flow path between the two. As Figure 1as shown by the inlet guide vanes 1-1 and 1-2
[0036] (2) Provide a fulcrum for the rotor of the test turbine 4. For the test turbine 4, its rotor requires at least two front and rear fulcrums. The inner casing inside the inlet section can serve as the load-bearing frame for the front fulcrum of the rotor, provide support for the rotor, and transfer the radial and axial loads of the turbine rotor to the outer casing through the guide vanes between the inner and outer casings. As Figure 1 shown, the inlet guide vane 1-1 provides support for the test piece bearing 2.
[0037] (3) Provide a passage for the gas supply pipeline of the test turbine 4. Due to the relatively high inlet temperature of current high-performance turbines, it is usually necessary to introduce cooler gas into the turbine for cooling. In order to simulate the interaction between the cold gas and the mainstream gas during component tests, the test piece needs to be designed with a corresponding gas supply pipeline. Part of the cold gas needs to enter the turbine from below the turbine flow path, so this part of the pipeline needs to pass through the turbine flow path. In order to avoid large aerodynamic losses caused by the pipeline being directly exposed in the mainstream channel, guide vanes with excellent aerodynamic shapes are generally designed in the flow channel to envelope the pipeline. The guide vanes isolate the mainstream gas from the gas supply pipeline, on the one hand, avoiding large aerodynamic losses, and on the other hand, also suppressing the heating effect of the relatively high-temperature mainstream gas on the cold gas in the pipeline. As Figure 1 shown, the cold gas supply pipeline 3 passes through the inlet guide vane 1-2, realizing the function of supplying gas to the turbine.
[0038] In summary, in order to achieve the above three functions, the inlet section needs to be designed with an inlet guide vane 1 (including inlet guide vanes 1-1 and 1-2).
[0039] Figure 2 shows the shape of the inlet guide vane 1. To achieve the guiding effect, the inlet guide vane 1 generally has a "drop shape" like an airplane wing.
[0040] As Figure 3 shown, for the flow path between two adjacent inlet guide vanes 1, the flow path width first contracts and then expands. The surface pressure of the corresponding inlet guide vane 1 first decreases and then increases. After the air flow passes through the maximum thickness position of the inlet guide vane 1 ( Figure 3 the position A shown), due to the decrease in the curvature of the guide vane, the air flow velocity decreases and the kinetic energy weakens. At the same time, due to the start of the expansion of the flow path, the air flow pressure increases, and the resistance faced by the air flow increases. When the kinetic energy of the air flow itself is not sufficient to resist the large flow resistance, the air flow will separate from the surface of the inlet guide vane 1 and then reverse flow occurs.
[0041] As Figure 4As shown, the top surface 13 of the inlet guide vane 1 before improvement is a straight section, and the inlet guide vane 1 is arranged on the inner annular surface (i.e., the inner casing 20). Since the radius of the flow passage gradually increases from the inside to the outside, the circumferential length of the annular flow passage increases, and the degree of expansion near the outer flow passage will be greater. Therefore, the risk of air flow separation at the outer flow passage position is higher.
[0042] As Figure 5 shown, flow separation occurs at the inlet guide vane 1 near the outer flow passage. Figure 5 In [FIGURE], a represents the flow separation line, 11 represents the leading edge of the vane 1, and 12 represents the trailing edge of the vane 1.
[0043] Figure 6 and Figure 7 [FIGURE] and [FIGURE] show the improved inlet guide vane 100 of the present invention. The inlet guide vane 100 includes opposite vane tips 110 and vane roots 120. As Figure 6 and Figure 7 shown, the upper side represents the vane tip 110 of the inlet guide vane 100, and the lower side represents the vane root 120 of the inlet guide vane 100. A top surface 111 is also provided at the vane tip 110. The top surface 111 is used to connect to the outer casing, and the vane root 120 is used to connect to the inner casing. At least part of the top surface 111 extends obliquely along the chord length direction towards the vane root 120 to the trailing edge 140 of the inlet guide vane 100.
[0044] The top surface 111 of the inlet guide vane 100 of the present invention is inclined towards the trailing edge 140, so that the top surface 111 contracts inwards. Compared with the inlet guide vane 1 with a straight top surface 13 before improvement, the present invention can reduce the degree of expansion of the outer flow passage, effectively inhibit the flow separation at the outer flow passage, and avoid large flow separation on the vane flow passage surface, which has an adverse impact on the tested turbine. It enables the vane profile to have an excellent aerodynamic shape and improves the aerodynamic performance of the guide vane.
[0045] As Figure 6 shown, the thickness of the inlet guide vane 100 gradually increases from the leading edge 130 and gradually decreases to the maximum thickness, that is, the cross-section of the inlet guide vane 100 of the present invention is in the shape of a water droplet as Figure 2 shown. The air flow in the flow passage flows in the direction from the Figure 7 left side to the right side in [FIGURE], Figure 7 the left side in [FIGURE] is the upstream of the flow passage, that is, at the leading edge 130 of the inlet guide vane 100; the right side is the downstream of the flow passage, that is, at the trailing edge 140 of the inlet guide vane 100.
[0046] Furthermore, as Figure 7As shown, the top surface 111 includes an un-inclined portion 111-a and an inclined portion 111-b. Among them, the un-inclined portion 111-a extends from the leading edge 130 of the inlet guide vane 100 to the maximum thickness, and the inclined portion 111-b extends from the maximum thickness to the trailing edge 140. The inclined portion 111-b inclines and extends towards the root of the vane along the chord length direction at the maximum thickness to the trailing edge 140.
[0047] The upstream flow surface (i.e., the top surface 111) of the inlet guide vane 100 of the present utility model is no longer a straight section after the maximum thickness, but contracts inward. As Figure 8 shown, the inlet guide vane 100 of the present utility model can reduce the degree of flow passage expansion after the maximum thickness of the outer flow passage vane, effectively inhibit the flow separation at the outer flow passage, and improve the aerodynamic performance.
[0048] In an embodiment, the inclined portion 111-b and the un-inclined portion 111-a are connected by an arc transition. As Figure 9 shown, a represents Figure 5 the flow separation line shown. The flow separation line a and the upstream flow passage (i.e., the un-inclined portion 111-a of the top surface 111 of the inlet guide vane 100) can form an included angle α. Figure 9 It is represented as 5 in
[0049] According to engineering practice, the included angle α between the inclined portion 111-b and the un-inclined portion 111-a of the top surface 111 is preferably 15° to 30°.
[0050] It should be noted that the position of the flow separation point 6 is the same as that of the maximum thickness, that is, the flow separation point 6 can be understood as the maximum thickness of the inlet guide vane 100.
[0051] Figure 10 shows the forming steps of the inlet guide vane 100 of the present utility model. Figure 11 shows the structure of the inlet guide vane 100 of the present utility model and the internal casing 20. The Figure 9 ray 7 and the circular arc section 9 in Figure 10 are formed into the rotary surface C around the central axis B-B of the internal casing 20, and then the upper right corner 1-3 of the inlet guide vane 1 before improvement is eliminated to form the optimized inlet guide vane 100 of the present utility model, as Figure 6 、 Figure 7 and Figure 11 shown.
[0052] Refer to Figure 1, the turbine component of the present utility model includes an outer casing 30, an inner casing 20, and the inlet guide vane 100 of any one of the above embodiments. The turbine component can be a turbine test piece. As Figure 12 shown, the top surface 111 of the inlet guide vane 100 is connected to the outer casing 30, and the vane root 120 of the inlet guide vane 100 is connected to the inner casing 20.
[0053] Continuing to refer to Figure 12 , in one embodiment, there are multiple inlet guide vanes 100, and the multiple inlet guide vanes 100 are arranged at intervals along the outer circumference of the inner casing 20. The number of the inlet guide vanes 100 can be selected from 8 to 10. A flow passage is formed between two adjacent inlet guide vanes 100, the outer casing 30, and the inner casing 20.
[0054] As Figure 12 shown, optionally, the inlet guide vane 100 can be welded to the outer casing 30 and the inner casing 20; the inlet guide vane 100, the outer casing 30, and the inner casing 20 can also be integrally cast and formed.
[0055] Although the present utility model is disclosed above with preferred embodiments, it is not intended to limit the present utility model. Any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the present utility model. Therefore, any modification, equivalent change, and decoration made to the above embodiments based on the technical essence of the present utility model without departing from the technical solution of the present utility model shall fall within the protection scope defined by the claims of the present utility model.
Claims
1. An imported guide vane, characterized in that, The inlet guide vane includes an opposite vane tip and a vane root; The inlet guide vane further includes a top surface provided at the vane tip; The top surface is used to connect to the external casing, and the vane root is used to connect to the internal casing; At least a part of the top surface extends obliquely towards the vane root in the chord length direction to the trailing edge of the inlet guide vane.
2. The inlet guide vane according to claim 1, characterized in that, The thickness of the inlet guide vane gradually increases from the leading edge and gradually decreases to the maximum thickness.
3. The inlet guide vane according to claim 2, characterized in that, The top surface includes an un-inclined part extending from the leading edge of the inlet guide vane to the maximum thickness and an inclined part extending from the maximum thickness to the trailing edge; The inclined part extends obliquely towards the vane root in the chord length direction at the maximum thickness to the trailing edge.
4. The inlet guide vane according to claim 3, wherein, The included angle between the inclined part and the un-inclined part of the top surface is 15° to 30°; 5. The inlet guide vane according to claim 3 or 4, characterized in that, The inclined part and the un-inclined part are connected by an arc transition; 6. The inlet guide vane according to claim 5, characterized in that, The radius of the arc at the arc transition connection is 20 to 90 mm; 7. A turbine component includes an outer casing and an inner casing, characterized in that, The turbine component further includes an inlet guide vane according to any one of claims 1 to 6; The top surface of the inlet guide vane is connected to the external casing, and the vane root of the inlet guide vane is connected to the internal casing; 8. The turbine component according to claim 7, wherein, There are multiple inlet guide vanes, and the multiple inlet guide vanes are arranged at intervals along the outer circumference of the internal casing; A flow passage is formed between two adjacent inlet guide vanes, the external casing, and the internal casing; 9. The turbine component according to claim 7 or 8, characterized in that, The inlet guide vane is welded to the external casing and the internal casing; 10. The turbine component according to claim 7 or 8, characterized in that, The inlet guide vane, the external casing, and the internal casing are integrally formed.