Visual high-pressure combustion chamber and turbine coupling experiment device

Abstract

The invention discloses a visual high-pressure combustion chamber and turbine coupling experiment device, and relates to the technical field of aero-engines, the visual high-pressure combustion chamber and turbine coupling experiment device comprises a combustion chamber outer casing, a combustion chamber inner casing and a turbine guide vane outer casing, the combustion chamber inner casing is arranged in the combustion chamber outer casing, and two sides of the combustion chamber outer casing are fixedly connected with inner quartz glass; external quartz glass observation windows are fixedly connected to the top and the two sides of the combustion chamber outer casing, the combustion chamber inner casing is communicated with the turbine guide vane outer casing through a connecting cavity, and a combustion chamber and turbine interface test interface is formed in the top of the connecting cavity. By means of the visual high-pressure combustion chamber and turbine coupling experiment device, parameters of a compact interface of a combustion chamber and a turbine can be obtained, aerodynamic heat transfer performance parameters of the turbine under the combustion working condition can be obtained, and combustion organizations and aerodynamic rules in the combustion chamber under the influence of turbine guide vanes can be obtained.

Description

Technical Field

[0001] The invention relates to the technical field of aeroengines, and in particular to a visualized high-pressure combustion chamber and turbine coupling experimental device. Background Art

[0002] With the continuous development of advanced aero-engine technology, higher requirements are placed on the overall power of the engine. As the two major hot end components of an aero-engine, the combustion chamber and turbine face greater challenges in their structural design optimization. Theoretically, for every 55K increase in the turbine inlet temperature, the engine thrust can be increased by 8%-13%, and the cycle efficiency can be increased by 2%-13%. In order to further improve the thrust boosting efficiency, advanced combustion chambers are developing towards the goal of high temperature boosting, with the head intake volume increasing continuously. At the same time, the combustion chamber outlet temperature is further increased, the strong turbulence characteristics are more obvious, and the influence of the unsteady hot spot at the combustion chamber outlet on the cooling structure design of the downstream turbine blades is more prominent. This shows that the strong coupling effect between the combustion chamber and the turbine is becoming increasingly urgent.

[0003] The design of the existing single-component experimental device is relatively mature. However, due to the lack of multi-component interaction effects, its experimental environment does not match the actual working environment of the combustion chamber and turbine. In comparison, the combustion chamber and turbine integrated experimental device can avoid this factor and is the basis for conducting coupling research. At present, the German Aerospace Center, Darmstadt University of Technology and others have established a coupling test bench for a full-ring combustion chamber and a 1.5-stage turbine, which can conduct experiments in a stage environment close to the actual engine working conditions and conduct research on the gas-thermal performance and coupling matching of the combustion chamber and the turbine. However, it has the problems of high cost and difficulty in testing, and it is impossible to conduct mechanistic visualization experiments. Compared with the former, the multi-head combustion chamber and turbine integrated experimental device has lower cost and more friendly testing, and is a better choice for conducting laboratory-scale coupling system research. The University of Florence and the University of Oxford have built a mature multi-head coupled guide vane system test bench, which can conduct research on the influence of gas-thermal parameters and cooling performance in the turbine flow channel under the combined action of swirl and turbulence. However, it simulates hot spots under non-reaction conditions and simplifies the structures of the combustion chamber, so it is impossible to conduct high-temperature experiments considering chemical reactions. In addition, there is currently no integrated test bench for combustion chamber and turbine guide vanes that can carry out visualization experiments under high temperature and high pressure. Summary of the invention

[0004] The purpose of the present invention is to solve the defects in the prior art and to propose a visual high-pressure combustion chamber and turbine coupling experimental device.

[0005] In order to achieve the above object, the present invention adopts the following technical solutions:

[0006] A visualized high-pressure combustion chamber and turbine coupling experimental device comprises an outer casing of a combustion chamber, an inner casing of a combustion chamber and an outer casing of a turbine guide vane, wherein the inner casing of the combustion chamber is arranged inside the outer casing of the combustion chamber, internal quartz glass is fixedly connected to both sides of the outer casing of the combustion chamber, external quartz glass observation windows are fixedly connected to the top and both sides of the outer casing of the combustion chamber, the inner casing of the combustion chamber is connected to the outer casing of the turbine guide vane through a connecting cavity, and a combustion chamber and turbine interface test interface is arranged on the top of the connecting cavity.

[0007] Furthermore, an installation groove is provided on the inner wall of the casing inside the combustion chamber, and the flame tube is embedded in the installation groove through a hook and fixed by a flame tube fixing cover plate.

[0008] Furthermore, a swirler is provided on the inner casing of the combustion chamber, and the swirler is arranged on a side of the flame tube away from the outer casing of the turbine guide vane.

[0009] Furthermore, a fuel pipe fixing seat is arranged on the outer casing of the combustion chamber, the fuel pipe passes through the fuel pipe fixing seat and is connected to the swirler, a fuel nozzle is arranged at the end of the fuel pipe, and the swirler is provided in multiple groups, and one group of swirlers corresponds to one group of fuel pipes.

[0010] Furthermore, an ignition needle fixing seat is provided at the bottom of the outer casing of the combustion chamber, an ignition needle is provided on the ignition needle fixing seat, the ignition needle extends into the inner casing of the combustion chamber, and the ignition needle floating ring is provided below the flame tube.

[0011] Furthermore, guide vane accompanying blocks are arranged on both sides of the connecting cavity, a plurality of groups of turbine guide vanes are arranged in the connecting cavity, and a guide vane air inlet cavity is formed at the bottom of the connecting cavity.

[0012] Furthermore, a water-cooled rectifying blade grid is arranged in the outlet cavity of the turbine guide vane outer casing.

[0013] Beneficial Effects

[0014] Compared with the prior art, the present invention has the following beneficial effects:

[0015] The visualization experimental device of the combustion chamber and turbine can obtain the parameters of the compact interface between the combustion chamber and the turbine, obtain the aerodynamic heat transfer performance parameters of the turbine under combustion conditions, and obtain the combustion organization and aerodynamic laws in the combustion chamber under the influence of the turbine guide vanes.

[0016] A guide vane cooling structure with separate air supply is designed, and a water cooling structure is designed for the exhaust section, which can meet high temperature and high pressure experimental conditions.

[0017] The multi-head combustion chamber is designed with a double-layer quartz structure. The inner layer of quartz is heat-resistant and the outer layer of quartz is pressure-resistant. It can maintain the periodicity of the center head under real high temperature and high pressure conditions, which is closer to the actual experimental conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The accompanying drawings are used to provide further understanding of the present invention and constitute a part of the specification. They are used to explain the present invention together with the embodiments of the present invention and do not constitute a limitation of the present invention.

[0019] Figure 1 This is a schematic diagram of the overall structure of the combustion chamber and turbine experimental device.

[0020] Figure 2 A vertical cross-sectional view of the combustion chamber and turbine experimental apparatus.

[0021] Figure 3 It is a horizontal cross-sectional view of the combustion chamber and turbine experimental device.

[0022] In the figure: 1 - combustion chamber outer casing, 2 - external quartz glass observation window, 3 - fuel pipe fixing seat, 4 - fuel nozzle, 5 - ignition needle fixing seat, 6 - combustion chamber inner casing, 7 - swirler, 8 - flame tube plate, 9 - ignition needle floating ring, 10 - flame tube fixing cover plate, 11 - internal quartz glass, 12 - internal quartz glass cover plate, 13 - turbine guide vane outer casing, 14 - turbine guide vane, 15 - guide vane companion block, 16 - guide vane inlet cavity, 17 - combustion chamber and turbine interface test interface, 18 - water-cooled straightening blade. DETAILED DESCRIPTION

[0023] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0024] In the description of the present invention, it is necessary to understand that the terms "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship are based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0025] Reference Figure 1 - Figure 3A visualized high-pressure combustion chamber and turbine coupling experimental device comprises an outer casing 1 of a combustion chamber, an inner casing 6 of a combustion chamber and an outer casing 13 of a turbine guide vane. The inner casing 6 of the combustion chamber is arranged in the outer casing 1 of the combustion chamber. Internal quartz glass 11 is fixedly connected to both sides of the outer casing 1 of the combustion chamber. The internal quartz glass 11 is fixed by an internal quartz glass cover plate 12. External quartz glass observation windows 2 are fixedly connected to the top and both sides of the outer casing 1 of the combustion chamber. The inner casing 6 of the combustion chamber is connected to the outer casing 13 of the turbine guide vane through a connecting cavity. A combustion chamber and turbine interface test interface 17 is arranged on the top of the connecting cavity.

[0026] The device uses double-layer quartz glass. The inner layer of glass is used to withstand the high temperature of the main combustion zone of the combustion chamber. The pressure difference on both sides of the glass is that the head pressure drop is relatively small. The outer layer of glass is not affected by 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.

[0027] The device uses double-layer quartz glass. The inner layer of glass is used to withstand the high temperature of the main combustion zone of the combustion chamber. The pressure difference on both sides of the glass is that the head pressure drop is relatively small. The outer layer of glass is not affected by 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.

[0028] Observation windows are arranged on three sides of the outer casing 1 of the combustion chamber of the device, and observation windows are arranged on two sides of the inner casing 6 of the combustion chamber, which is convenient for arranging the laser optical path and photography and video equipment to adapt to PIV (particle image velocimetry) and / or PLIF (laser induced fluorescence method) laser diagnostic technology and infrared temperature measurement technology.

[0029] In other preferred embodiments, a mounting groove is provided on the inner wall of the casing 6 inside the combustion chamber, the flame tube is embedded in the mounting groove through a hook, and is fixed by a flame tube fixing cover plate 10 .

[0030] The inner casing 6 of the combustion chamber of the device is located inside the outer casing 1 of the combustion chamber, and the upper and lower flame tube plates 8 (the combustion chamber of the aircraft engine is an annular combustion chamber, and the inner and outer flame tubes are replaced by upper and lower annular tubes. For the single swirler single-head combustion chamber, there is no cylindrical flame tube. This device replaces the ring with a rectangle, so the upper and lower flame tubes are used instead.) The hook structure is inserted into the slot of the inner casing 6 of the combustion chamber, and the flame tube fixing cover plate 10 is connected to the inner casing 6 of the combustion chamber by bolts and nuts to fix the flame tube plate 8, so the flame tube plate 8 can be replaced. At the same time, a cooling hole structure is designed on the flame tube fixing cover plate 10, so as to prevent the side wall from being burned by high temperature. Among them, the flame tube plate 8 can be a detachable component, and the combustion organization in the flame tube can be changed by changing the position of the large hole and the cooling hole.

[0031] In other preferred embodiments, a swirler is provided on the inner casing of the combustion chamber, and the swirler is provided on a side of the flame tube away from the outer casing of the turbine guide vane.

[0032] Furthermore, a fuel pipe fixing seat is provided on the combustion chamber outer casing, the fuel pipe passes through the fuel pipe fixing seat and is connected to the swirler, a fuel nozzle is provided at the end of the fuel pipe, and multiple groups of swirlers are provided, and one group of swirlers is correspondingly provided with a group of fuel pipes. As an example, the fuel nozzle 4 is a detachable component, and different pressure conditions can be matched by replacing the fuel nozzle 4. The swirler 7 can be a detachable component, and the swirl number can be adjusted and the flame tube pressure drop can be controlled by changing the blade thickness, installation angle, height, and hub ratio of the swirler 7.

[0033] In other preferred embodiments, guide vane accompanying blocks 15 are arranged on both sides of the connecting cavity, a plurality of groups of turbine guide vanes 14 are arranged in the connecting cavity, and a guide vane air inlet cavity 16 is formed at the bottom of the connecting cavity.

[0034] The device fixes the turbine guide vane blades and the guide vane companion block 15 to the guide vane air inlet cavity 16 by bolts, and then inserts the guide vane air inlet cavity 16 from bottom to top into the turbine guide vane outer casing 13 and fixes it by bolts and graphite gaskets, so that the cooling air intake of the turbine guide vane can be controlled separately. The combustion chamber outer casing 1 and the turbine guide vane outer casing 13 are connected to the inlet and outlet pipes by bolts and nuts, and sealed by graphite gaskets. Among them, the turbine guide vane 14 can be a detachable component, and the cooling form and efficiency of the turbine guide vane surface can be changed by changing the air film hole structure and blade profile of the turbine guide vane surface.

[0035] In other preferred embodiments, an ignition needle fixing seat 5 is provided at the bottom of the combustion chamber outer casing 1, an ignition needle is provided on the ignition needle fixing seat 5, the ignition needle extends into the combustion chamber inner casing 6, and the ignition needle floating ring 9 is provided below the flame tube.

[0036] In other preferred embodiments, a water-cooled straightening blade cascade 18 is provided in the outlet cavity of the turbine guide vane outer casing 13. The water-cooled straightening blade cascade 18 is inserted into the turbine guide vane outer casing 13 from the right side and fixed to its flange by bolts and nuts, thereby preventing the outlet channel pipeline from being ablated by high temperature.

[0037] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A visual high-pressure combustion chamber and turbine coupling experimental device, characterized in that: It includes an outer casing of a combustion chamber, an inner casing of a combustion chamber and an outer casing of a turbine guide vane. The inner casing of the combustion chamber is arranged inside the outer casing of the combustion chamber. Internal quartz glass is fixedly connected to both sides of the outer casing of the combustion chamber. External quartz glass observation windows are fixedly connected to the top and both sides of the outer casing of the combustion chamber. The inner casing of the combustion chamber is connected to the outer casing of the turbine guide vane through a connecting cavity, and a combustion chamber and turbine interface test interface is arranged on the top of the connecting cavity.

2. A visualized high-pressure combustion chamber and turbine coupling experimental device according to claim 1, characterized in that: The inner wall of the casing inside the combustion chamber is provided with a mounting groove, the flame tube is embedded in the mounting groove through a hook, and is fixed by a flame tube fixing cover plate.

3. A visualized high-pressure combustion chamber and turbine coupling experimental device according to claim 1, characterized in that: A swirler is arranged on the inner casing of the combustion chamber, and the swirler is arranged on a side of the flame tube away from the outer casing of the turbine guide vane.

4. A visualized high-pressure combustion chamber and turbine coupling experimental device according to claim 3, characterized in that: A fuel pipe fixing seat is arranged on the combustion chamber outer casing, the fuel pipe passes through the fuel pipe fixing seat and is connected to the swirler, a fuel nozzle is arranged at the end of the fuel pipe, and the swirler is arranged in multiple groups, and one group of swirlers is correspondingly arranged with one group of fuel pipes.

5. The visual high-pressure combustion chamber and turbine coupling experimental device according to claim 1, characterized in that: An ignition needle fixing seat is arranged at the bottom of the outer casing of the combustion chamber, an ignition needle is arranged on the ignition needle fixing seat, the ignition needle extends into the inner casing of the combustion chamber, and the ignition needle floating ring is arranged below the flame tube.

6. The visualized high-pressure combustion chamber and turbine coupling experimental device according to claim 1 is characterized in that: Guide vane accompanying blocks are arranged on both sides of the connecting cavity, a plurality of groups of turbine guide vanes are arranged in the connecting cavity, and a guide vane air inlet cavity is formed at the bottom of the connecting cavity.

7. The visualized high-pressure combustion chamber and turbine coupling experimental device according to claim 1 is characterized in that: A water-cooled straightening cascade is arranged in the outlet cavity of the turbine guide vane outer casing.

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