Turbine guide vane inlet and outlet temperature circumferential scanning measurement device coupled with multi-head fan-shaped backflow combustion chamber

Abstract

The invention discloses a turbine guide vane inlet and outlet temperature circumferential scanning measurement device coupled with a multi-head fan-shaped backflow combustion chamber, and relates to the technical field of aero-engines. Comprising a guide vane inlet single eight-point temperature probe, a guide vane outlet single eight-point temperature probe, a rotating shaft, rotating shaft flanges, a servo steering engine, a displacement mechanism and a gland, the guide vane inlet single-branch eight-point temperature probe and the guide vane outlet single-branch eight-point temperature probe are installed in through holes of the two rotating shafts correspondingly, and the tops of the guide vane inlet single-branch eight-point temperature probe and the guide vane outlet single-branch eight-point temperature probe penetrate through a fan-shaped limiting groove in the bottom of the combustion chamber outer case and extend to the inlet section and the outlet section of the turbine guide vane in the combustion chamber outer case correspondingly. According to the invention, the single eight-point temperature probe at the inlet and outlet of the guide vane can perform circumferential scanning and temperature measurement by controlling the servo steering engine, so that the temperature parameters of the cross sections of the inlet and outlet of the guide vane in the ultra-compact backflow combustion chamber and turbine guide vane coupling system under high-temperature and high-pressure conditions are obtained.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engine, in particular to a turbine guide vane inlet and outlet temperature circumferential scanning measurement device coupled with a multi-head sector-shaped backflow combustion chamber. BACKGROUND

[0002] Since the late 1980s, the turbine inlet temperature of aero-engine has been greatly improved due to the rapid progress of material technology and cooling technology. With the increase of high-pressure turbine inlet temperature, the hot spot phenomenon and its influence become more and more obvious, and the internal flow and heat transfer mechanism of the turbine becomes more complex. Since the turbine inlet temperature field distribution has a great influence on the internal unsteady flow and heat transfer characteristics, the research on the turbine inlet hot spot migration phenomenon not only has an important guiding role for turbine cascade cooling structure design and cooling air flow selection, but also is extremely critical for the overall gas-thermal performance of the aero-engine. It is a key content that must be considered in the turbine cascade aerodynamic optimization design and high-efficiency cooling technology research. Therefore, the research on the turbine guide vane inlet and outlet temperature circumferential scanning measurement method coupled with the multi-head sector-shaped backflow combustion chamber has important theoretical and engineering significance for improving the thermal protection and service reliability of the high-temperature components of the engine.

[0003] Designing and building an experimental platform integrating the combustion chamber and the turbine guide vane is the basis for in-depth research on the coupling between the two, which can provide reliable experimental data support for numerical simulation methods, and help to reveal the gas-thermal performance variation law of the combustion chamber and the migration process of the hot spot in the turbine passage in the coupling system. The German Aerospace Center, Oxford University and Darmstadt University of Technology have respectively established a coupling experimental platform integrating a full-ring combustion chamber and a 1.5-stage turbine, which realizes experimental research under the condition close to the actual engine working condition, and provides a theoretical and experimental basis for the gas-thermal performance and coupling matching of the combustion chamber and the turbine. However, such platforms have the problems of high construction and operation cost and high test complexity. In contrast, the experimental platform integrating the multi-head combustion chamber and the turbine has lower cost and more convenient test conditions, and becomes a more preferred scheme for researching the aerodynamic and thermal coupling system at the laboratory scale. At present, the more mature multi-head coupling experimental platforms in the world include the three-head six-guide vane sector-shaped device built by the University of Florence and the two-head four-guide vane rectangular experimental platform built by the University of Oxford, which can carry out research on the aerodynamic and thermal parameters and cooling characteristics in the turbine passage under the action of swirl and turbulence and other actions. In addition, there is no experimental platform integrating the combustion chamber and the turbine guide vane that can carry out inlet and outlet temperature field scanning measurement at high temperature and high pressure at present. Therefore, it is urgent to design a turbine guide vane inlet and outlet temperature circumferential scanning measurement device coupled with a multi-head sector-shaped backflow combustion chamber. SUMMARY

[0004] The present application mainly aims to provide a turbine guide vane inlet and outlet temperature circumferential scanning measurement device coupled with a multi-head sector-shaped backflow combustion chamber to overcome the problems in the prior art.

[0005] To solve the above technical problems, the present application adopts the following technical solutions: A turbine guide vane inlet and outlet temperature circumferential scanning measurement device coupled with a multi-head sector-shaped backflow combustion chamber, comprising a guide vane inlet single-branch eight-point temperature probe, a guide vane outlet single-branch eight-point temperature probe, a rotating shaft, a rotating shaft flange, a servo steering engine, a displacement mechanism and a Gland head, the displacement mechanism is installed at the bottom of the combustion chamber outer casing, two rotating shaft flanges are respectively installed on the two sides of the displacement mechanism, one end of the rotating shaft is rotatably installed on the rotating shaft flange, and the other end extends into the interior of the displacement mechanism, the guide vane inlet single-branch eight-point temperature probe and the guide vane outlet single-branch eight-point temperature probe are respectively installed in the through holes of the two rotating shafts, the top portions of the two penetrating through the sector-shaped limiting slot at the bottom of the combustion chamber outer casing extend to the inlet cross section and the outlet cross section of the turbine guide vane inside the combustion chamber outer casing respectively, and the lead wires at the bottom of the two are led out from the interior of the displacement mechanism through the Gland head. The servo steering engine is used to drive the rotating shaft to rotate, thereby driving the guide vane inlet single-branch eight-point temperature probe and the guide vane outlet single-branch eight-point temperature probe to swing and perform circumferential scanning temperature measurement on the turbine guide vane inlet and outlet cross sections.

[0006] Further, rotating shaft top screws are threadedly installed in the interiors of the two rotating shafts, and the ends of the two rotating shaft top screws abut against the outer walls of the guide vane inlet single-branch eight-point temperature probe and the guide vane outlet single-branch eight-point temperature probe to fix the same.

[0007] Further, a star-shaped gasket is sleeved on the outside of the rotating shaft, bolt holes are formed in the corresponding positions of the rotating shaft flange and the displacement mechanism, and the inside of the rotating shaft flange is pressed against the star-shaped gasket after the two are connected.

[0008] Further, the servo steering engine is fixedly installed on the outside of the rotating shaft flange, and the servo steering engine is in transmission connection with the rotating shaft through a star-shaped key.

[0009] Further, the displacement mechanism comprises a main shell and a bottom plate connected to the bottom of the main shell.

[0010] Further, the Gland head is installed on the bottom plate and is used to lead out the lead wires of the guide vane inlet single-branch eight-point temperature probe and the guide vane outlet single-branch eight-point temperature probe and realize air-tight sealing.

[0011] Further, the interior of the main shell is provided with a water cooling channel and a guide vane air cooling collection cavity, the water cooling channel is arranged in the double-layer wall of the main shell, and the guide vane air cooling collection cavity is arranged in the middle upper part of the main shell.

[0012] Further, the outer diameters of the guide vane inlet single-branch eight-point temperature probe and the guide vane outlet single-branch eight-point temperature probe are 5 mm, and the inner diameter of the through hole of the rotating shaft is 5.2 mm.

[0013] Further, the interior of the combustion chamber outer casing is also provided with a flame tube.

[0014] Compared with the prior art, the present application has the following beneficial effects: The present application drives the rotating shaft to rotate through the servo steering engine, so as to drive the guide vane inlet single-branch eight-point temperature probe and the guide vane outlet single-branch eight-point temperature probe of the turbine guide vane inlet and outlet to perform circumferential scanning temperature measurement, so as to obtain the temperature parameters of the guide vane inlet and outlet cross section in the ultra-compact backflow combustion chamber and turbine guide vane coupling system under high temperature and high pressure conditions, obtain the turbine aerodynamic heat transfer performance parameters under different outlet hot spot working conditions, and obtain the combustion organization and aerodynamic law in the combustion chamber under the influence of the turbine guide vane. The present application designs the guide vane inlet single-branch eight-point temperature probe and the guide vane outlet single-branch eight-point temperature probe with an outer diameter of 5 mm to perform circumferential scanning temperature measurement, which can greatly reduce the interference of the temperature probe on the internal flow field of the combustion chamber and the turbine guide vane, so as to be more close to the real experimental conditions. The present application designs a separate guide vane cooling structure, and designs a water cooling structure in the double-layer wall of the displacement mechanism, so as to meet the high temperature and high pressure experimental conditions. BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 It is a whole structure schematic view of the turbine guide vane inlet and outlet temperature circumferential scanning measurement device of the present application.

[0016] Figure 2 It is a structure schematic view of the device connected with the combustion chamber outer casing of the present application.

[0017] Figure 3 It is a front view of the device connected with the combustion chamber outer casing of the present application.

[0018] Figure 4 It is a side view of the device connected with the combustion chamber outer casing of the present application.

[0019] Figure 5 It is a Figure 3 A-A section view of the present application.

[0020] Figure 6 It is a Figure 4 B-B section view of the present application.

[0021] Figure 7 For the present invention Figure 5 A magnified view of the lower middle section.

[0022] Figure 8 This is a schematic diagram of the rotating shaft structure of the present invention.

[0023] Figure 9 This is a schematic diagram of the rotating flange structure of the present invention.

[0024] Explanation of reference numerals in the attached drawings: 1-Outer casing of the combustion chamber, 2-Flame tube, 3-Turbine guide vane, 4-Single eight-point temperature probe at the guide vane inlet, 5-Single eight-point temperature probe at the guide vane outlet, 6-Shaft, 7-Shaft set screw, 8-Star washer, 9-Shaft flange, 10-Servo motor, 11-Displacement mechanism, 12-Gran head, 13-Sector-shaped limit groove. Detailed Implementation

[0025] The technical solution of the present invention will be further described below with reference to the accompanying drawings and embodiments.

[0026] Combination Figures 1 to 9 This embodiment provides a circumferential scanning measurement device for the inlet and outlet temperatures of a turbine guide vane coupled to a multi-head fan-shaped recirculation combustion chamber. It includes a single eight-point temperature probe 4 at the guide vane inlet, a single eight-point temperature probe 5 at the guide vane outlet, a rotating shaft 6, a rotating shaft flange 9, a servo motor 10, a displacement mechanism 11, and a grate head 12. The displacement mechanism 11 is installed at the bottom of the outer casing 1 of the combustion chamber. Two rotating shaft flanges 9 are respectively installed on both sides of the displacement mechanism 11. One end of the rotating shaft 6 is rotatably mounted on the rotating shaft flange 9, and the other end extends into the interior of the displacement mechanism 11. The single eight-point temperature probe 5 at the guide vane inlet... Eight-point temperature probe 4 and single eight-point temperature probe 5 at the guide vane outlet are respectively installed in the through holes of two rotating shafts 6. The tops of both extend through the fan-shaped limiting groove 13 at the bottom of the combustion chamber 1 to the inlet and outlet sections of the turbine guide vane 3 inside. The leads at the bottom of both are led out from the inside of the displacement mechanism 11 through the granite head 12. The servo motor 10 is used to drive the rotating shaft 6 to rotate, causing the single eight-point temperature probe 4 at the guide vane inlet and the single eight-point temperature probe 5 at the guide vane outlet to swing and perform circumferential scanning temperature measurement at the inlet and outlet sections of the turbine guide vane 3.

[0027] Specifically, the sector-shaped limiting groove 13 can limit the single eight-point temperature probe 4 at the guide vane inlet and the single eight-point temperature probe 5 at the guide vane outlet, restricting their swing stroke. Since the lower middle part of the single eight-point temperature probe 4 at the guide vane inlet and the single eight-point temperature probe 5 at the guide vane outlet is a lead wire, it can deform. Therefore, even if the lead wire is fixedly connected to the Grand head 12, it will not affect the rotation of the single eight-point temperature probe 4 at the guide vane inlet and the single eight-point temperature probe 5 at the guide vane outlet.

[0028] In a further embodiment of the present application, the inner part of the two rotating shafts 6 are threaded with rotating shaft jacks 7, the ends of the two rotating shaft jacks 7 are respectively abutted against the outer wall of the guide vane inlet single eight-point temperature probe 4 and the guide vane outlet single eight-point temperature probe 5 to fix them.

[0029] In a further embodiment of the present application, the outer part of the rotating shaft 6 is sleeved with a star washer 8, the rotating shaft flange 9 and the displacement mechanism 11 are respectively provided with bolt holes at the corresponding positions, and the inner part of the rotating shaft flange 9 is pressed against the star washer 8 after the two are connected. Specifically, the star washer 8 is used to achieve the effect of shaft sealing under high pressure.

[0030] In a further embodiment of the present application, the servo steering engine 10 is fixedly installed on the outer side of the rotating shaft flange 9, and the servo steering engine 10 is in transmission connection with the rotating shaft 6 through the star-shaped key. When the servo steering engine 10 is in transmission connection with the rotating shaft 6 through the star-shaped key, the rotating shaft flange 9 has already pressed the star washer 8, so that the rotating shaft 6 rotates under the condition of shaft sealing.

[0031] In a further embodiment of the present application, the outer diameter of the guide vane inlet single eight-point temperature probe 4 and the guide vane outlet single eight-point temperature probe 5 is 5mm, and the inner diameter of the through hole of the rotating shaft 6 is 5.2mm. By adopting this scheme, after the temperature probe passes through the through hole of the rotating shaft 6, it needs to be fixed by the rotating shaft jack 7. Because the size is small, the interference of the temperature probe to the internal flow field of the combustion chamber and the turbine guide vane can be greatly reduced, so as to be more close to the real experimental condition.

[0032] In the present application, the displacement mechanism 11 includes a main shell and a bottom plate connected to the bottom of the main shell. Specifically, the gran head 12 is installed on the bottom plate, which is used to lead out the lead wire of the guide vane inlet single eight-point temperature probe 4 and the guide vane outlet single eight-point temperature probe 5 and realize air tightness. The inner part of the main shell is provided with a water cooling channel and a guide vane gas cooling collection chamber, the water cooling channel is arranged in the double-layer wall of the main shell, and the guide vane gas cooling collection chamber is arranged in the middle and upper part of the main shell.

[0033] By adopting the design of the water cooling channel and the guide vane gas cooling collection chamber, the high temperature and high pressure experimental conditions can be met. Specifically, the water cooling channel in the double-layer wall of the main shell plays a cooling role and can effectively cope with the overheating problem of the device under high temperature working condition; the guide vane gas cooling collection chamber is provided, cooling gas enters from here, passes through the water-cooled rectifier grid, and enters the inside of the turbine guide vane 3 to cool the turbine guide vane, which effectively improves the ablation of the guide vane surface under high temperature working condition.

[0034] In the present application, the combustion chamber outer casing 1 is provided with guide vane accompanying blocks on both sides, and the inner part is provided with a flame tube 2 and multiple turbine guide vanes 3.

[0035] Specifically, the inner wall of the combustion chamber outer casing 1 is provided with a mounting groove, the flame tube 2 is embedded in the mounting groove through a mortise and tenon structure, and is fixed through a flame tube fixing cover plate. The turbine guide vane 3 and the guide vane accompanying block are fixed to the combustion chamber outer casing 1 through bolts, and then the guide vane cooling cavity is inserted into the combustion chamber outer casing 1 from bottom to top and is fixed through bolts and graphite gaskets, so that the cooling air intake of the turbine guide vane can be controlled separately. Among them, the turbine guide vane 3 can be a detachable component, and the cooling form and efficiency of the turbine guide vane surface can be changed by changing the turbine guide vane surface film hole structure and blade profile.

[0036] In further embodiments, a water-cooled rectification vane array is arranged in the outlet cavity of the combustion chamber outer casing 1, so as to prevent the outlet passage pipeline from being ablated by high temperature.

[0037] When the device of the embodiment works, the servo steering engine 10 is controlled by the PLC automatic control system, the guide vane inlet single eight-point temperature probe 4 and the guide vane outlet single eight-point temperature probe 5 are rotated by 3° every 15 seconds to record a group of temperature data, and the rotation accuracy can reach within ±0.1°. The temperature field data of the turbine guide vane inlet and outlet sector section within 60° are scanned to fully include the temperature data of the multi-head center periodic area.

[0038] The above is only the preferred embodiment of the present application, and does not limit the technical scope of the present application. Any slight modification, equivalent change and modification of the above embodiment according to the technical essence of the present application still belongs to the scope of the technical solution of the present application.

Claims

1. A turbine vane inlet and outlet temperature circumferential scan measurement device coupled with a multi-head sector-shaped reverse-flow combustion chamber, characterized in that, The single eight-point temperature probe of guide vane inlet (4), the single eight-point temperature probe of guide vane outlet (5), the rotating shaft (6), the rotating shaft flange (9), the servo steering engine (10), the displacement mechanism (11) and the gran head (12) are included, the displacement mechanism (11) is installed at the bottom of the combustion chamber outer casing (1), two rotating shaft flanges (9) are installed on the two sides of the displacement mechanism (11) respectively, one end of the rotating shaft (6) is rotatably installed on the rotating shaft flange (9), the other end extends to the inside of the displacement mechanism (11), the single eight-point temperature probe of guide vane inlet (4) and the single eight-point temperature probe of guide vane outlet (5) are installed in the through hole of the rotating shaft (6) respectively, the top of the two extends to the inlet section and the outlet section of the turbine guide vane (3) inside the combustion chamber outer casing (1) respectively through the fan-shaped limiting slot (13) at the bottom of the combustion chamber outer casing (1), the lead wire at the bottom of the two is led out from the inside of the displacement mechanism (11) through the gran head (12); Wherein, the servo steering engine (10) is used for driving the rotating shaft (6) to rotate, and drives the single eight-point temperature probe of guide vane inlet (4) and the single eight-point temperature probe of guide vane outlet (5) to swing and scan the temperature of the inlet and outlet sections of the turbine guide vane (3) circumferentially.

2. A turbine vane inlet and outlet temperature circumferential scan measuring device coupled to a multi-head sector-shaped reverse-flow combustion chamber as claimed in claim 1, characterized in that, The inside of the rotating shaft (6) is screwedly provided with a rotating shaft top screw (7), and the ends of the two rotating shaft top screws (7) abut against the outer walls of the single eight-point temperature probe of guide vane inlet (4) and the single eight-point temperature probe of guide vane outlet (5) to fix the same.

3. A turbine vane inlet and outlet temperature circumferential scan measuring device coupled to a multi-head sector-shaped reverse-flow combustion chamber as claimed in claim 1, characterized in that, The outside of the rotating shaft (6) is provided with a star washer (8), bolt holes are formed in the corresponding positions of the rotating shaft flange (9) and the displacement mechanism (11), and the inside of the rotating shaft flange (9) is pressed against the star washer (8) after the two are connected.

4. A turbine vane inlet and outlet temperature circumferential scan measuring device coupled to a multi-head sector-shaped reverse-flow combustion chamber as defined in claim 1, wherein, The servo steering engine (10) is fixedly installed on the outside of the rotating shaft flange (9), and the servo steering engine (10) is in transmission connection with the rotating shaft (6) through a wrench key.

5. A turbine vane inlet and outlet temperature circumferential scan measuring device coupled to a multi-head sector-shaped reverse-flow combustion chamber as defined in claim 1, wherein, The displacement mechanism (11) comprises a main shell and a bottom plate connected to the bottom of the main shell.

6. A turbine vane inlet and outlet temperature circumferential sweep measurement device coupled to a multi-head sector-shaped reverse-flow combustion chamber as claimed in claim 5, characterized in that, The gran head (12) is installed on the bottom plate and is used for leading out the lead wires of the single eight-point temperature probe of guide vane inlet (4) and the single eight-point temperature probe of guide vane outlet (5) and realizing air tightness.

7. A turbine vane inlet and outlet temperature circumferential sweep measurement device coupled to a multi-head sector-shaped reverse-flow combustion chamber as claimed in claim 5, characterized in that, The inside of the main shell is provided with a water cooling channel and a guide vane gas cooling collection cavity, the water cooling channel is arranged in the double-layer wall inside of the main shell, and the guide vane gas cooling collection cavity is arranged in the middle upper portion of the main shell.

8. A turbine vane inlet and outlet temperature circumferential scan measuring device coupled to a multi-head sector-shaped reverse-flow combustion chamber as defined in claim 1, wherein, The outer diameters of the single eight-point temperature probe of guide vane inlet (4) and the single eight-point temperature probe of guide vane outlet (5) are 5 mm, and the inner diameter of the through hole of the rotating shaft (6) is 5.2 mm.

9. A turbine vane inlet and outlet temperature circumferential scan measuring device coupled to a multi-head sector-shaped reverse-flow combustion chamber as defined in claim 1, wherein, The inside of the combustion chamber outer casing (1) is further provided with a flame tube (2).

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