Adjustable air inlet pre-rotation structure for gas turbine disc cavity test
By designing an adjustable intake pre-rotating structure, the problems of uneven intake air and complex guide vanes in the gas turbine disk chamber test are solved, and the pressure uniformity and test efficiency in the intake chamber are improved, simplified the test process and reduced costs.
Patent Information
- Application Number
- CN202510410713.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-02
- Publication Date
- 2025-08-01
AI Technical Summary
In the test of existing gas turbine disc chambers, the intake air intake and the complex design of the guide vane lead to unstable operation of the rotor, high processing costs, and difficult to adapt to changes in different working conditions.
An adjustable air intake pre-rotating structure is designed, including an intake flange, an air collection chamber and a removable screw sleeve pre-rotating hole. By adjusting the screw sleeve, the tangential speed of the air intake under different working conditions is achieved. The screw sleeve is threadedly connected to the receiver. The screw sleeve structure is externally six square, which is convenient to replace to adjust the flow cross-section.
It achieves uniform pressure in the intake chamber, reduces intake losses, improves the operating efficiency and stability of the test pieces, simplifies the test process, and reduces costs.
Smart Images
Figure CN120404152A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of intake pre-whirl structures, and particularly relates to an adjustable intake pre-whirl structure for a gas turbine disk cavity test. Background Art
[0002] When developing large gas turbines, in order to reduce the difficulty of development, component performance tests need to be carried out for each component. The disk cavity test is specifically used to simulate and test the real flow path of the air system in a heavy gas turbine, and is an important test for obtaining the flow parameters along the disk cavity inside the gas turbine, verifying the accuracy of the secondary air system design scheme, and obtaining the flow characteristics of flow components.
[0003] In the disk cavity test, a pipeline perpendicular to the rotor axis is usually used for simulating intake. This scheme has a simple structure and low processing cost, and its structural schematic diagram is as shown in Figure 1 However, during the operation of the rotor, the air flow perpendicular to the center of rotation will have a large impact on the rotor, thus affecting the running stability of the rotor. At the same time, it is easy to have uneven intake when directly intaking air from different intake ports, which is not conducive to restoring the real air system of the gas turbine. Existing intake pre-whirl technical solutions usually form a vortex by designing and installing pre-whirl guide vanes, and the inlet air flow is guided to the intake cavity through the pre-whirl guide vanes. However, one type of guide vane can only correspond to one working condition. Once the working condition changes, the entire guide vane mounting frame needs to be replaced. Moreover, the shape of the guide vane is complex, and a set of guide vane designs need to be completed relying on professional two-dimensional and three-dimensional design software and design processes. This leads to high design difficulty and processing difficulty of the guide vane, greatly prolonging the test design, processing, and testing time. However, each guide vane scheme can only be aimed at one intake scheme, and the guide vane has high design difficulty, high processing difficulty, and high cost. Summary of the Invention
[0004] The purpose of the present invention is to overcome the deficiencies of the prior art and provide an adjustable intake pre-whirl structure for a gas turbine disk cavity test.
[0005] The purpose of the present invention is achieved by the following technical solutions: The present invention discloses an adjustable intake pre-whirl structure for a gas turbine disk cavity test, including an intake flange and a gas collecting cavity. A casing is arranged on the gas collecting cavity, and intake pre-whirl holes are arranged on the casing. The air flow enters the gas collecting cavity through the intake flange and then enters the intake cavity through the intake pre-whirl holes. The intake pre-whirl holes are arranged at a preset angle with the radial direction.
[0006] Further, the diameter of the intake pre-whirl holes is 3.9 - 4.1 mm, the intake mass flow rate is 0.266 kg / s, and the number of intake pre-whirl holes is 12.
[0007] Further, the intake pre-whirl holes are of a detachable screw sleeve structure.
[0008] Preferably, the end of the sleeve structure is an external hexagonal structure.
[0009] Preferably, the sleeve has an external thread and is threadedly connected to the casing. By replacing different sleeves, the change of the flow cross-section size at this position can be realized.
[0010] The beneficial effects of the present invention are as follows: 1) The present invention improves the problems of difficult design, processing and testing of the test intake air. The intake flanges are circumferentially evenly distributed. After the air flow passes through the intake flanges, it first enters the air collecting chamber formed by the outer ring of the air collecting chamber and the casing, and then enters the intake chamber through the intake pre-whirl holes on the casing, so as to ensure that the pressure in the intake chamber is uniform in the circumferential direction. The intake pre-whirl holes are at a certain angle with the radial direction, so as to form a tangential velocity component. By adjusting the aperture of the intake pre-whirl holes, the tangential velocity values required for the intake air under different design conditions can be respectively achieved.
[0011] 2) The intake structure of the present invention can effectively reduce the intake loss, improve the efficiency and stability margin during the operation of the test piece. At the same time, the adjustable intake structure makes the test simpler and faster, and improves the economic benefits of the test bench. Brief Description of the Drawings
[0012] Figure 1 It is a schematic diagram of the disk cavity test structure of the prior art; Figure 2 It is a schematic diagram of the installation structure of the replaceable sleeve for the intake pre-whirl of the embodiment of the present invention; Figure 3 It is a schematic diagram of the special tooling for the installation of the sleeve of the embodiment of the present invention; In the figure, 1 - sleeve, 2 - casing, 3 - hexagonal groove, 4 - special tool, 5 - flow cross-section. Detailed Embodiment
[0013] Next, the technical solutions of the present invention will be clearly and completely described in conjunction with the embodiments. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative efforts fall within the protection scope of the present invention.
[0014] The present invention discloses an adjustable intake pre-whirl structure for a gas turbine disk cavity test, including an intake flange and an air collecting chamber. A casing is arranged on the air collecting chamber, and intake pre-whirl holes are arranged on the casing. The air flow enters the air collecting chamber through the intake flange and enters the intake chamber through the intake pre-whirl holes. The intake pre-whirl holes are arranged at a preset angle with the radial direction. The preset angle is not limited to a specific value, but is an angle preset according to the specific working environment.
[0015] Specifically, the diameter of the intake pre - swirl holes is 3.9 - 4.1 mm, the intake mass flow rate is 0.266 kg / s, and the number of intake pre - swirl holes is 12. The present invention realizes intake by designing a specific pre - swirl angle and designs a replaceable intake port. The design process of the pre - swirl angle is shown in Table 1. Different gas parameters can achieve different intake tangential Mach numbers at different angles, thereby reducing intake losses.
[0016] Table 1: Design process of pre - swirl angle Specifically, in order to meet the requirements of different experimental conditions, some of the intake pre - swirl holes are made into a replaceable bushing 1 structure. For example, the bushing 1 has an external thread of M20×1.5. The bushing 1 is thread - connected to the casing 2. By replacing different bushings 1, the size of the flow cross - section 5 at this position can be changed from 0 to φ17. The schematic diagram of the replaceable bushing installation structure is as Figure 2 shown. The intake flange is set in an inclined form with an angle consistent with that of the intake pre - swirl holes. When replacement is needed, the intake flange is opened to replace the bushing 1 to achieve different intake flow cross - sectional areas, thereby adjusting the intake speed. The end of the bushing 1 is an external hexagonal structure and is installed by a special tooling 4. The end of the tooling is provided with a hexagonal groove 3 and is magnetized. During installation, the bushing 1 is directly adsorbed on the end of the special tooling 4 for installation. The schematic diagram of the special tooling for bushing installation is as Figure 3 shown.
[0017] The present invention improves the problems of difficult design, processing, and testing of the test intake. The intake flanges are circumferentially evenly distributed. After the air flow passes through the intake flanges, it first enters the air - collecting cavity formed by the outer ring of the air - collecting cavity and the casing, and then enters the intake cavity through the intake pre - swirl holes on the casing, so as to ensure that the pressure in the intake cavity is uniform circumferentially. The intake pre - swirl holes form a certain angle with the radial direction to form a tangential velocity component. By adjusting the aperture of the intake pre - swirl holes, the tangential velocity values required for intake under different design conditions can be achieved respectively.
[0018] The above - mentioned are only the preferred embodiments of the present invention. It should be understood that the present invention is not limited to the form disclosed herein, should not be regarded as excluding other embodiments, but can be used in various other combinations, modifications, and environments, and can be changed within the scope of the concept described herein through the above teachings or the technology or knowledge in related fields. And any changes and modifications made by those skilled in the art without departing from the spirit and scope of the present invention should be within the protection scope of the appended claims of the present invention.
Claims
1. An adjustable intake pre-whirl structure for a gas turbine disk cavity test, characterized in that It includes an intake flange and a plenum chamber. A casing is provided on the plenum chamber, and intake pre-whirl holes are provided on the casing. Airflow enters the plenum chamber through the intake flange and then enters the intake chamber through the intake pre-whirl holes. The intake pre-whirl holes are set at a preset angle with respect to the radial direction.
2. The adjustable intake pre-whirl structure for gas turbine disk cavity test according to claim 1, wherein: The diameter of the intake pre-whirl holes of the intake pre-whirl holes is 3.9 - 4.1 mm, the intake mass flow rate is 0.266 kg / s, and the number of intake pre-whirl holes is 12.
3. The adjustable inlet pre-whirl structure for a gas turbine disk cavity test according to claim 1, characterized in that: The intake pre-whirl holes are detachable screw sleeves.
4. An adjustable intake pre-whirl structure for a gas turbine disk cavity test according to claim 3, characterized in that: The end of the screw sleeve is an external hexagonal structure.
5. The adjustable inlet pre-whirl structure for a gas turbine disk cavity test according to claim 4, characterized in that: The screw sleeve has an external thread and is threadedly connected to the casing. By replacing different screw sleeves, the change of the flow cross-section size at this position can be realized.