Reflux combustion chamber and turbine coupling experiment device with controllable outlet hot spot radial position

Abstract

The invention discloses a backflow combustion chamber and turbine coupling experiment device with a controllable outlet hot spot radial position, and belongs to the technical field of aero-engines, the backflow combustion chamber and turbine coupling experiment device comprises a combustion chamber outer casing, two sides of the combustion chamber outer casing are provided with first internal quartz glass; the combustion chamber outer casing is also provided with a combustion chamber and turbine interface test interface; the flame tube is located in the combustion chamber outer casing, second inner quartz glass is arranged on the two sides of the flame tube, and the first inner quartz glass and the second inner quartz glass are arranged in a one-to-one correspondence mode. A double-layer quartz structure is designed in the multi-head combustion chamber, the inner-layer quartz is resistant to temperature, the outer-layer quartz is resistant to pressure, test data under the real high-temperature and high-pressure working condition can be obtained, meanwhile, the periodicity of the center head is kept, and the test condition is closer to the real test condition.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine technology, specifically relating to an experimental device for coupling a reflow combustion chamber and a turbine with controllable radial position of the outlet hot spot. Background Technology

[0002] Due to the synergistic effects of its structural characteristics, combustion organization, and cooling mechanism, the recirculating combustor of an aero-engine exhibits significant temperature field inhomogeneity at the combustor exit, resulting in localized high-temperature core regions, or "hot spots." When these hot spots enter the high-pressure turbine, different migration paths can cause severe overheating in localized areas of the turbine guide vane surface, even leading to ablation failure. Particularly in the recirculating combustor, the high-temperature airflow generates centrifugal flow along small bends, making it easier for hot spots to distribute in the upper region of the guide vanes, thus exacerbating the risk of ablation at the blade tips. Therefore, studying the migration characteristics of hot spots and methods for controlling their radial position under strong coupling conditions between the combustor and turbine guide vanes is of significant theoretical and engineering importance for improving the thermal protection and service reliability of high-temperature engine components.

[0003] While the design of existing single-component experimental devices is relatively mature, their experimental environment does not accurately reflect the actual working environment of a combustion chamber and turbine due to the lack of multi-component interaction effects. In contrast, integrated combustion chamber and turbine experimental devices can avoid this factor and are fundamental for conducting coupling effect research. Currently, the German Aerospace Center (DLR) and the Technical University of Darmstadt have established coupled experimental rigs for a full-annular combustion chamber and a 1.5-stage turbine, enabling experiments to be conducted in environments close to real engine operating conditions to study the aero-thermal performance and coupling matching of the combustion chamber and turbine. However, these rigs suffer from high costs and testing difficulties, and cannot perform mechanistic visualization experiments. Multi-head integrated combustion chamber and turbine experimental devices are relatively cheaper and more user-friendly, making them a better choice for conducting laboratory-scale coupled system research. The University of Florence and the University of Oxford have built mature multi-head coupled guide vane system experimental rigs, capable of studying the effects of combined swirling and turbulent flow on aero-thermal parameters and cooling performance within the turbine flow channel. However, these rigs simulate hot spots under non-reactive conditions and simplify the various structures of the combustion chamber, making it impossible to conduct high-temperature experiments considering chemical reactions. Furthermore, there is currently no integrated test rig for combustion chambers and turbine guide vanes that can be used to conduct visual experiments under high temperature and high pressure. Summary of the Invention

[0004] To solve the above problems, the present invention adopts the following technical solution:

[0005] An experimental device for coupling a recirculating combustion chamber and a turbine with controllable radial position of the outlet hot spot includes:

[0006] The combustion chamber outdoor unit casing has first internal quartz glass on both sides; the combustion chamber outdoor unit casing also has a test interface for the combustion chamber and turbine interface.

[0007] The flame tube is located inside the outer casing of the combustion chamber. A second internal quartz glass is provided on both sides of the flame tube, wherein the first internal quartz glass and the second internal quartz glass are provided in a one-to-one correspondence.

[0008] A mixing hole assembly for an outer ring of a flame tube, wherein the mixing hole assembly for an outer ring of a flame tube is disposed on the outer ring surface of the flame tube;

[0009] A mixing hole assembly for an inner ring of a flame tube, wherein the mixing hole assembly for an inner ring of a flame tube is disposed on the inner ring surface of the flame tube;

[0010] Turbine guide vanes are embedded in the internal grooves of the combustion chamber outer casing to achieve a compact connection with the flame tube.

[0011] A fuel injection assembly, which is disposed on one side of the combustion chamber outside the combustion chamber, is used to inject fuel into the flame tube;

[0012] An ignition needle is disposed on the top of the outer casing of the combustion chamber; the ignition end of the ignition needle is located inside the flame tube to ignite the fuel in the flame tube.

[0013] Furthermore, the flame tube outer ring mixing hole assembly is disassembled and assembled through the threaded hole on the outer ring surface of the flame tube;

[0014] The mixing hole assembly of the inner ring of the flame tube is disassembled and assembled through the threaded hole on the inner ring surface of the flame tube.

[0015] Furthermore, the fuel injection assembly includes a fuel line holder, a fuel nozzle, and a fuel line;

[0016] The fuel pipe mounting bracket is mounted on the outer casing of the combustion chamber, and the fuel nozzle is located inside the flame tube; the end of the fuel pipe passes through the fuel pipe mounting bracket and is connected to the fuel nozzle.

[0017] Furthermore, a swirler is provided at the end of the flame tube, and the swirler is correspondingly arranged with the fuel nozzle to enhance the mixing of air and fuel and improve combustion efficiency.

[0018] Furthermore, guide vane accompanying blocks are provided on both sides of the interior of the combustion chamber; the turbine guide vane includes multiple sets of turbine guide vanes, which are disposed inside the combustion chamber.

[0019] Furthermore, an ignition needle holder is provided on the top of the combustion chamber, the ignition needle is mounted on the ignition needle holder, and the floating ring of the ignition needle is positioned above the flame tube.

[0020] Furthermore, a water-cooled rectifier blade grid is also provided in the outlet chamber of the combustion chamber to prevent the outlet channel pipeline from being burned by high temperature.

[0021] Furthermore, it also includes a displacement mechanism, which is connected to the bottom of the outer casing of the combustion chamber and forms a guide vane cooling air chamber.

[0022] Furthermore, the displacement mechanism includes a servo motor, which is connected to a multi-point temperature probe, which is disposed at the inlet and outlet of the turbine guide vane.

[0023] The servo motor drives a multi-point temperature probe to perform circumferential ring scanning temperature measurement, thereby obtaining the temperature field distribution of the turbine guide vane inlet and outlet sections.

[0024] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0025] The experimental device for controlling the radial position of the hot spot at the combustion chamber outlet, coupled with the turbine, can adjust the radial position of the hot spot at the combustion chamber outlet by changing the relative inlet area of ​​the inner and outer ring mixing holes of the flame tube through different combinations of these holes. This allows for the acquisition of turbine aerodynamic heat transfer performance parameters under different outlet hot spot radial positions, as well as the combustion organization and aerodynamic patterns within the combustion chamber under the influence of the turbine guide vanes.

[0026] The design incorporates a separately supplied air-cooled guide vane cooling chamber, and a water-cooled rectifier grating is also installed in the outlet chamber of the outer casing of the combustion chamber, which can meet the high-temperature and high-pressure experimental conditions.

[0027] The multi-head combustion chamber of this invention is designed with a double-layer quartz structure. The inner quartz layer is heat-resistant and the outer quartz layer is pressure-resistant, which can obtain test data under real high temperature and high pressure conditions, while maintaining the periodicity of the central head, which is closer to the real test conditions. Attached Figure Description

[0028] Figure 1 This is a vertical sectional view of the recirculation combustion chamber and turbine experimental setup;

[0029] Figure 2 This is a schematic diagram of the structure of the mixing hole assembly on the outer ring of the flame tube;

[0030] Figure 3 This is a schematic diagram of the structure of the inner ring mixing hole assembly of the flame tube;

[0031] Figure 4 This is a schematic diagram of the experimental setup for the recirculation combustion chamber and turbine.

[0032] In the diagram: 1 - Combustion chamber outer casing, 2 - Flame tube, 3 - Swirl, 4 - Ignition needle, 5 - Flame tube outer ring mixing hole assembly, 6 - Flame tube inner ring mixing hole assembly, 7 - Fuel nozzle, 8 - Fuel pipe mounting bracket, 9 - Turbine guide vane, 10 - Guide vane cooling chamber 5, 11 - Displacement mechanism, 12 - Multi-point temperature probe, 13 - Servo, 14 - Water-cooled rectifier blade, 15 - Flame tube large curved tube optical observation window, 16 - Guide vane exhaust section optical observation window. Detailed Implementation

[0033] Example 1

[0034] refer to Figure 1-4 An experimental device for coupling a recirculating combustion chamber and a turbine with controllable radial position of the outlet hot spot, comprising:

[0035] Combustion chamber outdoor casing 1, with first internal quartz glass on both sides; combustion chamber outdoor casing 1 is also provided with a test interface for the interface between the combustion chamber and the turbine.

[0036] Flame tube 2 is located inside the outer casing 1 of the combustion chamber. Both sides of the flame tube 2 are provided with second internal quartz glass, wherein the first internal quartz glass and the second internal quartz glass are provided in a one-to-one correspondence.

[0037] Flame tube outer ring mixing hole kit 5 is set on the outer ring surface of flame tube 2;

[0038] The inner ring mixing hole assembly 6 of the flame tube is set on the inner ring surface of the flame tube 2.

[0039] Turbine guide vanes are embedded in the internal grooves of the combustion chamber outer casing 1 to achieve a compact connection with the flame tube 2.

[0040] The fuel injection assembly is located on one side of the outer casing 1 of the combustion chamber and is used to inject fuel into the flame tube 2.

[0041] Ignition needle 4 is located on the top of the outer casing 1 of the combustion chamber; the ignition end of the ignition needle 4 is located inside the flame tube 2 to ignite the fuel in the flame tube 2.

[0042] In this embodiment, a flame tube large curved tube optical observation window 15 is fixedly connected to the rear side of the combustion chamber, and a guide vane exhaust section optical observation window 16 is fixedly connected to the exhaust section of the combustion chamber.

[0043] In this embodiment, the first inner quartz glass and the second inner quartz glass are double-layered quartz glass, which are used to withstand the high temperature of the main combustion zone of the combustion chamber. The pressure difference between the two sides of the glass is relatively small at the head. The outer glass is not affected by the high temperature and is mainly a pressure-bearing structure, thereby increasing the pressure-bearing range of the device and increasing the safety of the experimental device.

[0044] In this embodiment, the combustion chamber 1 and the flame tube 2 are provided with observation windows to facilitate the arrangement of laser optical paths and photography and video equipment, so as to adapt to PIV (particle image velocimetry) and / or PLIF (laser-induced fluorescence) laser diagnostic technology and infrared thermometry technology.

[0045] Preferably, the outer ring mixing hole assembly 5 of the flame tube 2 is disassembled and assembled through the threaded hole on the outer ring surface of the flame tube 2;

[0046] The inner ring mixing hole assembly 6 of the flame tube is disassembled and assembled through the threaded hole on the inner ring surface of the flame tube 2.

[0047] In this embodiment, the flame tube 2 is located inside the combustion chamber 1. It is inserted into the groove inside the combustion chamber 1 through a tenon and mortise structure, and is fixed by connecting the fixing cover plate of the flame tube 2 to the combustion chamber 1 through bolts and nuts.

[0048] In this embodiment, multiple sets of flame tube outer ring mixing hole kits 5 and 6 are provided. They can be disassembled and assembled through the threaded holes on the inner and outer ring surfaces of the flame tube 2. The relative air intake area of ​​the inner and outer ring mixing holes of the flame tube 2 can be adjusted. The flame tube outer ring mixing hole kits 5 and 6 are detachable components, and the combustion organization inside the flame tube can be changed by changing the relative air intake of the inner and outer ring mixing holes.

[0049] In this embodiment, the flame tube 2 is also provided with a cooling hole structure to prevent the wall surface from being burned by high temperature.

[0050] Preferably, the fuel injection assembly includes a fuel line holder 8, a fuel nozzle 7, and a fuel line;

[0051] The fuel pipe mounting bracket is installed on the outer casing 1 of the combustion chamber, and the fuel nozzle 7 is located inside the flame tube; the end of the fuel pipe passes through the fuel pipe mounting bracket and is connected to the fuel nozzle.

[0052] Preferably, a swirler 3 is provided at the end of the flame tube 2, and the swirler 3 is provided in correspondence with the fuel nozzle 7 to enhance the mixing of air and fuel and improve combustion efficiency.

[0053] In this embodiment, multiple sets of swirlers 3 and fuel injection assemblies are provided, with one set of swirlers corresponding to one set of fuel injection assemblies. The fuel nozzle 7 is detachably installed inside the flame tube 2, allowing for different pressure conditions to be matched by replacing the fuel nozzle 7. The swirlers 3 are also detachably installed inside the flame tube 2, and the number of swirls and the pressure drop of the flame tube 2 can be adjusted by changing the blade thickness, installation angle, height, and hub ratio of the swirlers 3. Preferably, three sets of swirlers 3 and fuel injection assemblies are provided.

[0054] Preferably, guide vane accompanying blocks are provided on both sides of the interior of the combustion chamber 1; the turbine guide vane includes multiple sets of turbine guide vanes 9, which are disposed inside the combustion chamber 1.

[0055] In this embodiment, the turbine guide vane blade 9 and the guide vane accompanying block are fixed to the combustion chamber outer casing 1 with bolts. Then, the guide vane cooling air chamber 10 is inserted into the combustion chamber outer casing 1 from bottom to top and fixed with bolts and graphite gaskets, thereby enabling independent control of the cooling air intake of the turbine guide vane. The turbine guide vane 9 is a detachable component; the cooling form and efficiency of the turbine guide vane surface can be changed by altering the air film perforation structure and blade profile.

[0056] Preferably, the top of the outer casing 1 of the combustion chamber is also provided with an ignition needle fixing seat, the ignition needle 4 is set on the ignition needle fixing seat, and the floating ring of the ignition needle is set above the flame tube 2.

[0057] Preferably, a water-cooled rectifier blade 14 is also provided in the outlet cavity of the combustion chamber 1 to prevent the outlet channel pipeline from being burned by high temperature.

[0058] Preferably, it also includes a displacement mechanism 11, which is connected to the bottom of the outer casing 1 of the combustion chamber and forms a guide vane cooling air chamber 10.

[0059] Preferably, the displacement mechanism 11 includes a servo motor 13, which is connected to a multi-point temperature probe, which is located at the inlet and outlet of the turbine guide vane.

[0060] The servo motor drives multiple temperature probes to perform circumferential ring scanning temperature measurement, thereby obtaining the temperature field distribution of the turbine guide vane inlet and outlet sections.

[0061] In this embodiment, a transmission structure is also included. The servo motor 13 and the transmission structure drive the multi-point temperature probe 12 to perform circumferential ring scanning temperature measurement, thereby obtaining the temperature field distribution of the turbine guide vane inlet and outlet sections. The transmission structure achieves the effect of shaft sealing under high pressure through a star-shaped gasket.

[0062] The above description is merely a preferred embodiment of the present invention and does not constitute any limitation on the technical scope of the present invention. Therefore, any minor modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention shall still fall within the scope of the technical solution of the present invention.

Claims

1. An experimental device for coupling a recirculating combustion chamber and a turbine with controllable radial position of the outlet hot spot, characterized in that, include: The combustion chamber outdoor unit casing has first internal quartz glass on both sides; the combustion chamber outdoor unit casing also has a test interface for the combustion chamber and turbine interface. The flame tube is located inside the outer casing of the combustion chamber. A second internal quartz glass is provided on both sides of the flame tube, wherein the first internal quartz glass and the second internal quartz glass are provided in a one-to-one correspondence. A mixing hole assembly for an outer ring of a flame tube, wherein the mixing hole assembly for an outer ring of a flame tube is disposed on the outer ring surface of the flame tube; A mixing hole assembly for an inner ring of a flame tube, wherein the mixing hole assembly for an inner ring of a flame tube is disposed on the inner ring surface of the flame tube; Turbine guide vanes are embedded in the internal grooves of the combustion chamber outer casing to achieve a compact connection with the flame tube. A fuel injection assembly, which is disposed on one side of the combustion chamber outside the combustion chamber, is used to inject fuel into the flame tube; An ignition needle is disposed on the top of the outer casing of the combustion chamber; the ignition end of the ignition needle is located inside the flame tube to ignite the fuel in the flame tube.

2. The experimental device for coupling a recirculating combustion chamber and a turbine with controllable radial position of the outlet hot spot according to claim 1, characterized in that, The flame tube outer ring mixing hole assembly is disassembled and assembled through the threaded hole on the outer ring surface of the flame tube; The mixing hole assembly of the inner ring of the flame tube is disassembled and assembled through the threaded hole on the inner ring surface of the flame tube.

3. The experimental device for coupling a recirculating combustion chamber and a turbine with controllable radial position of the outlet hot spot according to claim 1, characterized in that, The fuel injection assembly includes a fuel pipe mounting bracket, a fuel nozzle, and a fuel pipe. The fuel pipe mounting bracket is mounted on the outer casing of the combustion chamber, and the fuel nozzle is located inside the flame tube; the end of the fuel pipe passes through the fuel pipe mounting bracket and is connected to the fuel nozzle.

4. The experimental device for coupling a recirculating combustion chamber and a turbine with controllable radial position of the outlet hot spot according to claim 3, characterized in that, A swirler is provided at the end of the flame tube, and the swirler is correspondingly arranged with the fuel nozzle to enhance the mixing of air and fuel and improve combustion efficiency.

5. The experimental apparatus for coupling a recirculating combustion chamber and a turbine with controllable radial position of the outlet hot spot according to claim 1, characterized in that, The combustion chamber outer casing has guide vane accompanying blocks on both sides inside; the turbine guide vane includes multiple sets of turbine guide vanes, which are disposed inside the combustion chamber outer casing.

6. The experimental apparatus for coupling a recirculating combustion chamber and a turbine with controllable radial position of the outlet hot spot according to claim 1, characterized in that, The top of the combustion chamber is also provided with an ignition needle holder, the ignition needle is mounted on the ignition needle holder, and the floating ring of the ignition needle is positioned above the flame tube.

7. The experimental apparatus for coupling a recirculating combustion chamber and a turbine with controllable radial position of the outlet hot spot according to claim 1, characterized in that, The outlet chamber of the combustion chamber is also equipped with a water-cooled rectifier blade grid to prevent the outlet channel pipeline from being burned by high temperature.

8. The experimental apparatus for coupling a recirculating combustion chamber and a turbine with controllable radial position of the outlet hot spot according to claim 1, characterized in that, It also includes a displacement mechanism, which is connected to the bottom of the outer casing of the combustion chamber and forms a guide vane cooling air chamber.

9. The experimental apparatus for coupling a recirculating combustion chamber and a turbine with controllable radial position of the outlet hot spot according to claim 8, characterized in that, The displacement mechanism includes a servo motor, which is connected to a multi-point temperature probe, which is located at the inlet and outlet of the turbine guide vane. The servo motor drives a multi-point temperature probe to perform circumferential ring scanning temperature measurement, thereby obtaining the temperature field distribution of the turbine guide vane inlet and outlet sections.

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