Gas turbine secondary guider testing device

Abstract

The utility model provides a gas turbine secondary guider testing device, which belongs to the technical field of guider testing devices and comprises a mounting frame, an adjusting assembly and a fixing assembly. An air inlet flow channel is mounted at the top of the mounting frame; an air inlet guide cover is mounted at the front end of the air inlet flow channel; an annular seat is installed in an air inlet flow channel, a plurality of hinge seats are installed around the edge of one end of the annular seat, adjusting plates are hinged to the hinge seats through connectors installed at one ends of the adjusting plates, the adjusting plates are arranged around the annular seat, and the adjacent plate bodies are overlapped and sequentially arranged, and a driving ring is arranged on the outer ring of the annular seat. When an external driving structure drives the driving ring to rotate, the driving ring drives the guide column to move, so that the guide column drives the adjusting plate to perform variable-diameter adjustment relative to the annular seat, thereby changing the flow rate entering the air inlet flow channel, and testing different data according to the adjusted flow rate. Therefore, test data are enriched, and reference is improved.

Description

Technical Field

[0001] This utility model relates to the technical field of guide test devices, specifically a test device for a gas turbine second stage guide. Background Technology

[0002] The turbine guide vane is a crucial structural component designed to meet the requirements of high-performance aero engines. Its structure consists of a bladed flow channel forming the main gas flow channel of the turbine. A row of guide vanes and a subsequent row of rotor blades constitute a turbine stage. High-temperature gas enters the turbine guide vane from the annular combustion chamber outlet. The turbine guide vane compresses and deflects the high-temperature gas, driving the turbine rotor to perform work. The flow capacity of the turbine guide vane directly affects the performance of the aero engine. The turbine guide vane operates in harsh environments, bearing significant thermal stress caused by the high-temperature gas flow and uneven heating of various components, as well as aerodynamic forces generated when the gas passes through the guide vanes and vibration loads caused by airflow pulsation. The blade structure of the gas turbine second-stage guide vane is complex and contains internal pores. The surfaces requiring machining are the upper and lower surfaces and the two side surfaces. Before use, the turbine guide vane must undergo a flow capacity test. Typically, during the test, the airflow maintains a stable velocity after entering the test channel. The internal velocity of the flow channel cannot be adjusted during testing, resulting in single, less reliable test data. Utility Model Content

[0003] The purpose of this invention is to provide a gas turbine second-stage guide vane testing device to solve the problem mentioned in the background art that in conventional testing experiments, the airflow enters the test channel and maintains a stable flow velocity, and the flow velocity inside the channel cannot be controlled during testing, resulting in single and low reference value of the test data.

[0004] To achieve the above objectives, this utility model provides the following technical solution: a gas turbine second-stage guide vane testing device, comprising a mounting frame, an adjustment assembly, and a fixing assembly;

[0005] Wherein: an air intake channel is installed on the top of the mounting bracket, and an air intake guide cover is installed at the front end of the air intake channel;

[0006] The adjustment assembly includes an annular seat installed inside the air intake channel. Several hinge seats are installed around one edge of the annular seat. Several adjustment plates are provided on one side of the annular seat. A connector is fixedly installed at one end of each adjustment plate. The connector is hinged to the inside of the hinge seat by a pin. The adjustment plates are hinged around the annular seat and are arranged in an overlapping sequence. A drive ring is provided on the outer ring of the annular seat. A guide post is installed at one end of each adjustment plate. The guide post slides through the inside of the drive ring. The drive ring is connected to an external drive structure.

[0007] The fixed assembly includes a flange seat fixedly installed in the middle of the air intake channel. Servo cylinders are fixedly installed on both sides of the flange seat. A fixing rod is installed on the telescopic end of the servo cylinder. One end of the fixing rod passes through the flange seat and extends into the interior of the air intake channel. A secondary guide is fixed inside the flange seat by the fixing rod.

[0008] As a preferred embodiment of this utility model: the driving structure includes a gear ring fixedly installed at one end of the driving ring, a stepper motor is installed outside the air intake channel, a gear is fixedly installed at the output end of the stepper motor, the gear meshes with the gear ring, and a plurality of stroke grooves are opened around the surface of the driving ring, with the guide post inserted inside the stroke groove.

[0009] As a preferred embodiment of this utility model: an exhaust guide cover is fixedly installed at the tail end of the air intake channel, and pressure sensors are installed on the outer walls of the air intake guide cover, the air intake channel and the exhaust guide cover.

[0010] As a preferred embodiment of this utility model, a fairing is installed inside both the air intake fairing and the exhaust fairing.

[0011] As a preferred embodiment of this utility model: a part removal sealing plate is hingedly installed on the surface of the air intake channel near the flange seat.

[0012] As a preferred embodiment of this utility model: a limiting seat is fixedly installed in the middle of the surface of the annular seat, and the other end of the drive ring is rotatably installed inside the limiting seat.

[0013] Compared with the prior art, the beneficial effects of this utility model are:

[0014] (1) An annular seat is installed inside the inlet channel. Several hinge seats are installed around one edge of the annular seat. The adjustment plate is hinged to the hinge seat through a connector installed at one end. The adjustment plate is arranged around the annular seat and the adjacent plates overlap and are arranged in sequence. The outer ring of the annular seat is provided with a drive ring. One end of the adjustment plate is slidably inserted into the drive ring through a guide post. When the external drive structure drives the drive ring to rotate, the drive ring drives the guide post to move, so that the guide post drives the adjustment plate to adjust the diameter relative to the annular seat, thereby changing the flow rate inside the inlet channel. This makes it easier to test different data according to the adjusted flow rate, thereby enriching the test data and improving the reference value.

[0015] (2) The curved surface design of the front end of the fairing installed inside the air intake fairing ensures the flow field quality, reduces pressure loss during flow, and avoids interference such as shock waves. The tail end of the fairing installed inside the exhaust fairing is also curved, which makes the exhaust flow channel expand and ensures smooth exhaust. Attached Figure Description

[0016] Figure 1This is a schematic diagram of the overall structure of this utility model;

[0017] Figure 2 This is a cross-sectional structural diagram of the present invention;

[0018] Figure 3 This is a schematic diagram of the adjustment component structure of this utility model;

[0019] Figure 4 This is a schematic diagram of the fixing component structure of this utility model.

[0020] In the diagram: 1. Mounting bracket; 2. Inlet air passage; 3. Inlet air guide shroud; 4. Adjustment assembly; 41. Annular seat; 42. Hinge seat; 43. Adjustment plate; 44. Connector; 45. Drive ring; 46. Guide post; 5. Fixing assembly; 51. Flange seat; 52. Servo cylinder; 53. Fixing rod; 6. Gear ring; 7. Stepper motor; 8. Gear; 9. Stroke groove; 10. Exhaust guide shroud; 11. Pressure sensor; 12. Fairing; 13. Part removal sealing plate; 14. Limit seat. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0022] Please see Figures 1-4 A gas turbine second stage guide test device includes: a mounting frame 1, an adjustment assembly 4 and a fixing assembly 5; an air intake channel 2 is installed on the top of the mounting frame 1, and an air intake guide cover 3 is installed at the front end of the air intake channel 2.

[0023] Please see Figure 2 , Figure 3 The adjustment assembly 4 includes an annular seat 41 installed inside the air intake channel 2. Several hinge seats 42 are installed around one edge of the annular seat 41. Several adjustment plates 43 are provided on one side of the annular seat 41. A connector 44 is fixedly installed at one end of the adjustment plate 43. The connector 44 is hinged to the inside of the hinge seat 42 by a pin. The adjustment plates 43 are hinged around the annular seat 41 and adjacent adjustment plates 43 overlap and are arranged in sequence. A drive ring 45 is provided on the outer ring of the annular seat 41. A guide post 46 is installed at one end of the adjustment plate 43. The guide post 46 slides through the inside of the drive ring 45. The drive ring 45 is connected to an external drive structure.

[0024] In practical use: An annular seat 41 is installed inside the air intake channel 2. Several hinge seats 42 are installed around one edge of the annular seat 41. The adjusting plate 43 is hinged to the hinge seats 42 through a connector 44 installed at one end. The adjusting plate 43 is arranged around the annular seat 41 with adjacent plates overlapping and arranged in sequence. The outer ring of the annular seat 41 is provided with a drive ring 45. One end of the adjusting plate 43 is slidably inserted into the drive ring 45 through a guide post 46. When the external drive structure drives the drive ring 45 to rotate, the drive ring 45 drives the guide post 46 to move, so that the guide post 46 drives the adjusting plate 43 to adjust its diameter relative to the annular seat 41, thereby changing the flow rate inside the air intake channel 2. This makes it easier to test different data according to the adjusted flow rate, thereby enriching the test data and improving its reference value.

[0025] Please see Figure 4 The fixing component 5 includes a flange seat 51 fixedly installed in the middle of the air intake channel 2. Servo cylinders 52 are fixedly installed on both sides of the flange seat 51. A fixing rod 53 is installed on the telescopic end of the servo cylinder 52. One end of the fixing rod 53 passes through the flange seat 51 and extends into the interior of the air intake channel 2. A secondary guide is fixed inside the flange seat 51 by the fixing rod 53.

[0026] In practical use: The fixing component 5 includes a flange seat 51 installed in the middle of the air intake channel 2. Servo cylinders 52 are installed on both sides of the flange seat 51. When the servo cylinders 52 work, they drive the fixing rods 53 installed inside to move closer to the secondary guide inside the flange seat 51. The fixing rods 53 fix the secondary guide inside the air intake channel 2, which facilitates the testing of the secondary guide.

[0027] Please see Figure 2 , Figure 3 The drive structure includes a gear ring 6 fixedly installed at one end of the drive ring 45, a stepper motor 7 installed outside the air intake channel 2, a gear 8 fixedly installed at the output end of the stepper motor 7, the gear 8 meshing with the gear ring 6, a number of stroke grooves 9 are opened around the surface of the drive ring 45, a guide post 46 is inserted inside the stroke groove 9, a limit seat 14 is fixedly installed in the middle of the surface of the annular seat 41, and the other end of the drive ring 45 is rotatably installed inside the limit seat 14.

[0028] In practical use: The drive structure includes a gear ring 6 installed at one end of the drive ring 45. After the stepper motor 7 outside the air intake channel 2 rotates, it drives the gear 8 to rotate. The rotation of the gear 8 drives the meshing gear ring 6 to rotate. The gear ring 6 rotates inside the limiting seat 14 installed in the middle of the ring seat 41. Since the guide post 46 at one end of the adjusting plate 43 is inserted into the stroke groove 9 opened on the surface of the drive ring 45, when the drive ring 45 rotates, it drives the adjusting plate 43 to move on the hinge seat 42 through the guide post 46, thereby realizing the adjustment of the air intake volume.

[0029] Please see Figure 1 An exhaust guide shroud 10 is fixedly installed at the tail end of the intake air passage 2. Pressure sensors 11 are installed on the outer walls of the intake guide shroud 3, the intake air passage 2, and the exhaust guide shroud 10.

[0030] In practical use: an exhaust guide shroud 10 is installed at the tail end of the intake air passage 2. Pressure sensors 11 are installed on the outer walls of the intake guide shroud 3, the intake air passage 2 and the exhaust guide shroud 10 to monitor the pressure changes in the intake guide shroud 3, the intake air passage 2 and the exhaust guide shroud 10 under test conditions.

[0031] Please see Figure 2 Both the intake shroud 3 and the exhaust shroud 10 have fairings 12 installed inside.

[0032] In practical use: The curved design of the front end of the fairing 12 installed inside the intake fairing 3 ensures the quality of the flow field, reduces pressure loss during the flow process, and avoids interference such as shock waves. The tail end of the fairing 12 installed inside the exhaust fairing 10 is also curved, so that the exhaust end has an expanding trend, ensuring smooth exhaust.

[0033] Please see Figure 1 The surface of the air intake channel 2 is hinged to the flange seat 51 with a part removal sealing plate 13.

[0034] In practical use: The surface of the air inlet channel 2 is hinged to the flange seat 51 with a part removal sealing plate 13. The part removal sealing plate 13 facilitates the installation of the secondary guide inside the flange seat 51. After the test is completed, the part removal sealing plate 13 can be opened to facilitate the removal of the secondary guide.

[0035] An annular seat 41 is installed inside the air intake channel 2. Several hinge seats 42 are installed around one edge of the annular seat 41. An adjusting plate 43 is hinged to the hinge seats 42 through a connector 44 installed at one end. The adjusting plate 43 is arranged around the annular seat 41 with adjacent plates overlapping and arranged in sequence. A drive ring 45 is provided on the outer ring of the annular seat 41. One end of the adjusting plate 43 is slidably inserted into the drive ring 45 through a guide post 46. When the external drive structure drives the drive ring 45 to rotate, the drive ring 45 drives the guide post 46 to move, so that the guide post 46 drives the adjusting plate 43 to adjust its diameter relative to the annular seat 41, thereby changing the flow velocity entering the air intake channel 2. This makes it easier to test different data according to the adjusted flow velocity, thus enriching the test data and improving its reference value.

[0036] The contents not described in detail in this description are existing technologies known to those skilled in the art. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A gas turbine second-stage guide vane testing device, characterized in that, include: Mounting bracket (1), the top of which is equipped with an air intake channel (2), and the front end of which is equipped with an air intake guide cover (3). Adjustment assembly (4), the adjustment assembly (4) includes an annular seat (41) installed inside the air intake channel (2), a plurality of hinge seats (42) are installed around one end edge of the annular seat (41), a plurality of adjustment plates (43) are provided on one side of the annular seat (41), a connector (44) is fixedly installed at one end of the adjustment plate (43), the connector (44) is hinged to the inside of the hinge seat (42) by a pin, the adjustment plates (43) are hinged around the annular seat (41) and adjacent adjustment plates (43) are overlapped and arranged in sequence, the outer ring of the annular seat (41) is provided with a drive ring (45), a guide post (46) is installed at one end of the adjustment plate (43), the guide post (46) slides through the drive ring (45), and the drive ring (45) is connected to an external drive structure; The fixing component (5) includes a flange seat (51) fixedly installed in the middle of the air intake channel (2). Servo cylinders (52) are fixedly installed on both sides of the flange seat (51). A fixing rod (53) is installed on the telescopic end of the servo cylinder (52). One end of the fixing rod (53) passes through the flange seat (51) and extends into the air intake channel (2). A secondary guide is fixed inside the flange seat (51) by the fixing rod (53).

2. The gas turbine second-stage guide vane testing device according to claim 1, characterized in that: The drive structure includes a gear ring (6) fixedly installed at one end of the drive ring (45), a stepper motor (7) is installed on the outside of the air intake channel (2), a gear (8) is fixedly installed at the output end of the stepper motor (7), the gear (8) meshes with the gear ring (6), and a number of stroke grooves (9) are opened around the surface of the drive ring (45), and the guide post (46) is inserted inside the stroke groove (9).

3. The gas turbine second-stage guide vane testing device according to claim 1, characterized in that: An exhaust guide shroud (10) is fixedly installed at the tail end of the air intake channel (2), and pressure sensors (11) are installed on the outer walls of the air intake shroud (3), the air intake channel (2) and the exhaust guide shroud (10).

4. The gas turbine second-stage guide vane testing device according to claim 1, characterized in that: The air intake shroud (3) and the exhaust shroud (10) are both equipped with a fairing (12).

5. The gas turbine second-stage guide vane testing device according to claim 1, characterized in that: The surface of the air intake channel (2) is hinged to the flange seat (51) with a part removal sealing plate (13).

6. The gas turbine second-stage guide vane testing device according to claim 1, characterized in that: The limiting seat (14) is fixedly installed in the middle of the surface of the annular seat (41), and the other end of the drive ring (45) is rotatably installed inside the limiting seat (14).

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