Non-contact measurement structure for aero-engine combustion chamber outlet

Abstract

The invention discloses a non-contact measurement structure for an aero-engine combustion chamber outlet, and the structure comprises a measurement structure main body which is composed of a measurement structure inner wall and a measurement structure outer wall, and the top of the measurement structure outer wall is provided with an upper optical installation seat, a sensing head installation seat, and an outlet water pipe. A lower optical mounting base and an inlet water pipe are arranged at the bottom, an inlet flange is arranged at the left end of the lower optical mounting base, an outlet flange is arranged on the right side of the lower optical mounting base, a flow guide assembly is arranged between the inner wall and the outer wall of the measuring structure, and glass covers are arranged in the upper optical mounting base and the lower optical mounting base. An optical glass lens is arranged in the glass cover, and a cover plate is arranged on the glass cover. By means of the structure, high-temperature and high-pressure non-contact measurement of the outlet of the fan-shaped combustion chamber of the aero-engine can be achieved, engineering application research of non-contact optical measurement can be carried out under the high-temperature and high-pressure conditions of the outlet of the fan-shaped combustion chamber, and the reliability of pollution prevention and sealing protection of optical glass is high.

Description

Technical Field

[0001] The present invention relates to the technical field of measuring the temperature of an aero-engine combustion chamber outlet, and in particular to a non-contact measuring structure for an aero-engine combustion chamber outlet. Background Art

[0002] Combustion chamber outlet temperature is a crucial reference for aircraft engine performance evaluation. The need to advance technological development places increasingly stringent demands on its measurement. While contact-based measurement of combustion chamber outlet temperature is currently a popular topic, and the measurement structure is readily available, research on non-contact measurement of sector-shaped combustion chamber outlet temperature is relatively limited, and further development and optimization of non-contact measurement structures are needed.

[0003] Currently, the high-temperature and high-pressure non-contact measurement structure at the outlet of the fan-shaped combustion chamber of an aircraft engine needs to withstand the high-temperature and high-pressure combustion gas from the combustion chamber outlet; at the same time, it also faces the problem of gas leakage in the optical measurement channel and incomplete combustion leading to carbon deposition and contamination of the optical glass. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a non-contact measurement structure for the outlet of an aircraft engine combustion chamber; to solve the problems existing in the prior art such as the optical measurement channel being susceptible to contamination, flammable gas leakage, and difficulty in adapting to high temperature and high pressure environments, and to realize non-contact optical measurement of high temperature and high pressure at the outlet of a sector-shaped combustion chamber, while ensuring that the optical measurement channel is not contaminated and that the measured test data is true and valid.

[0005] In order to solve the above technical problems, the solution of the present invention is:

[0006] A non-contact measurement structure for an aircraft engine combustion chamber outlet, comprising a measurement structure main body formed by an inner wall and an outer wall of the measurement structure, an upper optical mount, a sensor head mount, and an outlet water pipe being provided at the top of the outer wall of the measurement structure, and a lower optical mount and an inlet water pipe being provided at the bottom, with an inlet flange provided at the left end and an outlet flange provided at the right end, a flow guide assembly being provided between the inner wall and the outer wall of the measurement structure, glass covers being provided within the upper and lower optical mounts, optical glass lenses being provided within the glass covers, a cover plate being provided on the glass cover, a sealing gasket A being provided between the glass cover and the optical glass lenses, a sealing gasket B being provided between the upper and lower optical mounts and between the cover plate and the glass cover, and a cooling air pipe being provided on the upper and lower optical mounts.

[0007] The glass cover and the cover plate are connected to the upper optical mounting seat and the lower optical mounting seat via M6 hexagon socket mounting bolts.

[0008] The sealing gasket A is a flexible graphite gasket with the dimensions of outer diameter×inner diameter×thickness=66mm×54mm×3mm, and the sealing gasket B is a copper gasket.

[0009] The inner rings of the upper optical mount and the lower optical mount are both evenly arranged with 50 air film holes, the diameter of the air film holes is 2 mm, and the air film holes are connected to the cold air pipe.

[0010] An interlayer water cavity is provided between the inner wall of the measuring structure and the outer wall of the measuring structure, and the flow guide component is provided inside the interlayer water cavity.

[0011] The guide assembly includes four guide plates, which are evenly arranged inside the interlayer water cavity, and each guide plate is provided with holes and slots.

[0012] The inlet flange and the outlet flange are both fan-shaped structures, and the inlet flange and the outlet flange are connected by M10 bolts.

[0013] The inlet flange is provided with a docking groove on the side away from the measurement structure body, and the outlet flange is provided with a docking boss on the side away from the measurement structure body.

[0014] The optical glass lens is an optical quartz glass lens of model JGS2, and the optical glass lens has a diameter of 64 mm, a thickness of 35 mm, and a pressure resistance of ≥3.0 MPa.

[0015] The diameters of the outlet water pipe, inlet water pipe and cooling air pipe are all 10 mm.

[0016] Compared with the prior art, the present invention has the following beneficial effects:

[0017] In this application, high-pressure cold air is introduced into the cold air pipe and blown toward the bottom of the optical glass through the upper optical mount, the lower optical mount and the inner ring air film hole, which can realize the anti-pollution function of the optical glass; the optical channel composed of the cover plate, the optical glass lens, the sealing gasket A, the sealing gasket B, the glass cover, the upper optical mount, the lower optical mount and the cold air pipe can effectively solve the problem of preventing the leakage of high-temperature and high-pressure gas, and can realize the role of non-contact optical measurement as a laser channel.

[0018] By using the measuring structure main body and the upper and lower optical mounts with windowed designs, the inlet flange of the fan-shaped structure with docking grooves and the outlet flange of the fan-shaped structure with docking bosses, the measuring structure of the present application and the fan-shaped combustion chamber are connected together with bolts, thereby realizing non-contact measurement of high-temperature and high-pressure gas at the outlet of the fan-shaped combustion chamber.

[0019] By designing the guide plate assembly, the low-speed backflow area in the water area of ​​the measuring section structure can be broken, the water flow can be guided to flow along the hot wall surface, and the cooling and heat exchange effect of the hot wall surface can be increased.

[0020] This application realizes high-temperature and high-pressure non-contact measurement of the outlet of the fan-shaped combustion chamber of an aircraft engine. The structure can carry out engineering application research of non-contact optical measurement in an environment where the maximum temperature at the outlet of the fan-shaped combustion chamber is not less than 2100K and the pressure is not less than 2.0MPa, and has high reliability in optical glass anti-pollution and sealing protection.

[0021] Through the interlayer water cavity design, cooling water is introduced through a low-inlet and high-outlet water supply method. The inner and outer walls of the measuring section are interconnected. The flow area and resistance loss of the flow channels of each component are limited by the combination of guide plates to achieve the purpose of distributing the circulating water volume. This can effectively increase the water flow velocity and solve the problems of high temperature and high pressure resistance. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a structural schematic diagram of the present invention;

[0023] Figure 2 is a cross-sectional view of the present invention;

[0024] Figure 3 Schematic diagram of the structure of the flow guide assembly in the present invention. DETAILED DESCRIPTION

[0025] The following is a further description of specific embodiments of the present invention in conjunction with the accompanying drawings. It should be noted that the description of these embodiments is intended to facilitate understanding of the present invention and does not constitute a limitation of the present invention. In addition, the technical features involved in the various embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.

[0026] like Figure 1-3 As shown, a non-contact measurement structure for an aircraft engine combustion chamber outlet includes a measurement structure body 5 formed by an inner wall 13 and an outer wall 12. The measurement structure body 5 is composed of the inner wall 13 and the outer wall 12, forming a sandwich water cavity 19 to facilitate the installation of four guide plates of the guide assembly 10. The four guide plates are evenly welded within the sandwich water cavity 19 and are provided with holes and slots. Circulating water at a pressure of approximately 0.4 MPa flows through the inlet water pipe 7 and the outlet water pipe 2 to cool and protect the measurement structure.

[0027] An upper optical mount 3, a sensor head mount 4 and an outlet water pipe 2 are provided on the top of the outer wall 5 of the measuring structure, and a lower optical mount 8 and an inlet water pipe 7 designed to be opposite to the upper optical mount 3 are provided at the bottom. An inlet flange 1 is provided at the left end, and an outlet flange 6 is provided at the right side. A guide component 10 is provided between the inner wall 13 of the measuring structure and the outer wall 12 of the measuring structure. Glass covers 9 are provided inside the upper optical mount 3 and the lower optical mount 8, and optical glass lenses 11 are provided inside the glass cover 9. A cover plate 14 is provided on the glass cover 9, and a sealing gasket A15 is provided between the glass cover 9 and the optical glass lens 11. Sealing gaskets B16 are provided between the upper optical mount 3, the lower optical mount 8 and the cover plate 14 and the glass cover 9. A cooling air pipe 17 is provided on the upper optical mount 3 and the lower optical mount 8.

[0028] The upper optical mount 3 and the lower optical mount 8 are used to cooperate with the glass cover 9 to install the optical glass lens 11. The glass cover 9 is then pressed with the cover plate 14. The cover plate, glass cover, upper optical mount 3 and lower optical mount 8 are then connected with M6 hexagon socket bolts and sealed with a sealing gasket A15. The sensor head mount 4 is installed on the top of the outer wall 5 of the measuring structure for the installation of a contact-type total temperature and total pressure composite sensor head, which facilitates comparison with the optical temperature measurement results.

[0029] Since the structure of the present invention is mainly in a high-temperature working environment of 2100K, an effective cooling design is required to ensure the working reliability of the system. Since the heat capacity of water is much higher than that of air, the cooling capacity of water per unit volume flow is stronger than that of air, and it can be recycled. Therefore, water cooling is adopted for the structural body 5, and the outlet water pipe 2, the inlet water pipe 7 and the guide assembly 10 are designed.

[0030] The present invention also considers that if the combustion chamber is not fully burned, the combustion gas may carry water vapor, oil mist, and carbon ash, which may contaminate the optical glass lens 11. This could cause the laser beam to scatter severely when passing through the glass, rendering it ineffective for measurement. Therefore, a cold air purge mechanism is designed. A φ10mm cold air pipe 17 is used to introduce cold air. The cold air pressure must be greater than the combustion gas pressure. Fifty φ2mm air film holes are evenly distributed around the inner ring of the optical mount to purge the optical glass lens 11. This forms an air film beneath the optical glass lens 11, preventing the combustion gas from engulfing and contaminating the optical glass lens 11.

[0031] The glass cover 9 and the cover plate 14 are connected to the upper optical mount 3 and the lower optical mount 8 by M6 hexagon socket mounting bolts. This arrangement is mainly for easy installation and disassembly, and the use of special hexagon socket mounting bolts can effectively reduce the possibility of conventional mis-disassembly.

[0032] Sealing gasket A15 is a flexible graphite gasket with the dimensions of outer diameter × inner diameter × thickness = 66mm × 54mm × 3mm, and sealing gasket B16 is a copper gasket. Flexible graphite gaskets and copper gaskets have remarkable pressure and high temperature resistance. At the same time, introducing cold air with a pressure greater than the gas pressure into the cold air pipe 17 can effectively solve the problem of gas leakage.

[0033] The inner rings of both the upper optical mount 3 and the lower optical mount 8 are evenly distributed with 50 air film holes, each with a diameter of 2 mm. These air film holes are connected to the cooling air pipe 17. These holes facilitate the purge of the optical glass lens 11, forming an air film beneath the lens to prevent the gas below from engulfing and contaminating the lens 11.

[0034] An interlayer water cavity is provided between the inner wall 13 of the measuring structure and the outer wall 12 of the measuring structure, and the flow guide component 10 is provided inside the interlayer water cavity 19 .

[0035] The measuring structure of the present invention adopts a sandwich water cavity design, and introduces cooling water through a low-inlet and high-outlet water supply method, so that the inner wall and outer wall of the measuring section are interconnected. The flow area and resistance loss of the flow channel of each component are limited by the combination of guide plates to achieve the purpose of distributing the circulating water volume, which can effectively increase the water flow rate.

[0036] The guide assembly 10 includes four guide plates, which are evenly arranged inside the interlayer water cavity 19 and are provided with holes and grooves.

[0037] In view of the situation in some areas where the water flow channel is too wide, the guide plate is too long and highly closed, resulting in the existence of low-speed recirculation area of ​​water flow, holes and slots are opened on the guide plate to break the low-speed recirculation area, guide the water flow along the hot wall surface, and increase the cooling and heat exchange effect.

[0038] The inlet flange 1 and the outlet flange 6 are both fan-shaped structures, and the inlet flange 1 and the outlet flange 6 are connected by M10 bolts.

[0039] The inlet flange 1 is provided with a docking groove 18 on the side away from the measurement structure body 5, and the outlet flange 6 is provided with a docking boss 20 on the side away from the measurement structure body 5.

[0040] By designing an inlet flange 1 of a fan-shaped structure with a docking groove 18 and an outlet flange 6 of a fan-shaped structure with a docking boss 20, the measurement structure of the present application and the fan-shaped combustion chamber are connected together by bolts, so as to realize non-contact measurement of high-temperature and high-pressure gas at the outlet of the fan-shaped combustion chamber.

[0041] The optical glass lens 11 is an optical quartz glass lens of model JGS2, and the optical glass lens 11 has a diameter of 64 mm, a thickness of 35 mm, and a pressure resistance of ≥3.0 MPa.

[0042] The diameters of the outlet water pipe 2, the inlet water pipe 7 and the cooling air pipe 17 are all 10 mm.

[0043] In the present application, high-pressure cold air is introduced into the cold air pipe 17, which is blown toward the bottom of the optical glass through the upper optical mount 3, the lower optical mount 8 and the inner ring air film hole, thereby realizing the anti-pollution function of the optical glass; the optical channel composed of the cover plate 14, the optical glass lens 11, the sealing gasket A15, the sealing gasket B16, the glass cover, the upper optical mount 3, the lower optical mount 8 and the cold air pipe 17 can effectively solve the function of preventing the leakage of high-temperature and high-pressure gas, and can realize the role of non-contact optical measurement as a laser channel.

[0044] By using the measuring structure main body 5 and the upper optical mount 3 and lower optical mount 8 with upper and lower window designs, the inlet flange 1 of the fan-shaped structure designed with a docking groove 18 and the outlet flange 6 of the fan-shaped structure designed with a docking boss 20, the measuring structure of the present application and the fan-shaped combustion chamber are connected together by bolts, so as to realize non-contact measurement of high-temperature and high-pressure gas at the outlet of the fan-shaped combustion chamber.

[0045] This application realizes high-temperature and high-pressure non-contact measurement of the outlet of the fan-shaped combustion chamber of an aircraft engine. The structure can carry out engineering application research of non-contact optical measurement in an environment where the maximum temperature at the outlet of the fan-shaped combustion chamber is not less than 2100K and the pressure is not less than 2.0MPa, and has high reliability in optical glass anti-pollution and sealing protection.

[0046] By designing the guide plate assembly 10, the low-speed backflow area in the water area of ​​the measuring section structure can be broken, and the water flow can be guided to flow along the hot wall surface, thereby increasing the cooling and heat exchange effect of the hot wall surface; through the interlayer water cavity design, cooling water is introduced through a low-inlet and high-outlet water supply method, the inner wall and the outer wall of the measuring section are interconnected, and the flow area and resistance loss of the flow channel of each component are limited by the guide plate combination to achieve the purpose of distributing the circulating water volume, which can effectively increase the water flow velocity and solve the problems of high temperature and high pressure resistance.

[0047] The embodiments of the present invention are described in detail above with reference to the accompanying drawings, but the present invention is not limited to the described embodiments. It is apparent to those skilled in the art that various changes, modifications, substitutions, and variations to these embodiments may be made without departing from the principles and spirit of the present invention, and these changes and modifications still fall within the scope of protection of the present invention.

Claims

1. A non-contact measurement structure for an aircraft engine combustion chamber outlet, characterized by: The invention comprises a measuring structure main body (5) composed of a measuring structure inner wall (13) and a measuring structure outer wall (12); an upper optical mounting seat (3), a sensing head mounting seat (4) and an outlet water pipe (2) are arranged on the top of the measuring structure outer wall (5); a lower optical mounting seat (8) and an inlet water pipe (7) are arranged on the bottom in a window-type design opposite to the upper optical mounting seat (3); an inlet flange (1) is arranged on the left end, and an outlet flange (6) is arranged on the right side; a flow guide component (10) is arranged between the measuring structure inner wall (13) and the measuring structure outer wall (12); the upper optical mounting seat (3) and the sensing head mounting seat (4) are arranged on the top of the measuring structure outer wall (5); A glass cover (9) is provided inside the optical mounting seat (3) and the lower optical mounting seat (8), an optical glass lens (11) is provided inside the glass cover (9), a cover plate (14) is provided on the glass cover (9), a sealing gasket A (15) is provided between the glass cover (9) and the optical glass lens (11), a sealing gasket B (16) is provided between the upper optical mounting seat (3), the lower optical mounting seat (8), the cover plate (14) and the glass cover (9), and a cooling air pipe (17) is provided on the upper optical mounting seat (3) and the lower optical mounting seat (8).

2. The non-contact measurement structure for an aircraft engine combustion chamber outlet according to claim 1, characterized in that: The glass cover (9) and the cover plate (14) are connected to the upper optical mounting seat (3) and the lower optical mounting seat (8) via M6 hexagon socket mounting bolts.

3. The non-contact measurement structure for an aircraft engine combustion chamber outlet according to claim 1, characterized in that: The sealing gasket A (15) is a flexible graphite gasket with the dimensions of outer diameter×inner diameter×thickness=66mm×54mm×3mm, and the sealing gasket B (16) is a copper gasket.

4. The non-contact measurement structure for an aircraft engine combustion chamber outlet according to claim 1, characterized in that: 50 air film holes are evenly arranged on the inner rings of the upper optical mounting seat (3) and the lower optical mounting seat (8), the diameter of the air film holes is 2 mm, and the air film holes are connected to the cold air pipe (17).

5. The non-contact measurement structure for an aircraft engine combustion chamber outlet according to claim 1, characterized in that: An interlayer water cavity is provided between the inner wall (13) of the measuring structure and the outer wall (12) of the measuring structure, and the flow guide component (10) is provided inside the interlayer water cavity (19).

6. The non-contact measurement structure for an aircraft engine combustion chamber outlet according to claim 1 or 5, characterized in that: The guide assembly (10) comprises four guide plates, the four guide plates being evenly arranged inside the interlayer water cavity (19), and the guide plates being provided with holes and slots.

7. The non-contact measurement structure for an aircraft engine combustion chamber outlet according to claim 1, characterized in that: The inlet flange (1) and the outlet flange (6) are both fan-shaped structures, and the inlet flange (1) and the outlet flange (6) are connected by M10 bolts.

8. The non-contact measurement structure for an aircraft engine combustion chamber outlet according to claim 1 or 7, characterized in that: The inlet flange (1) is provided with a docking groove (18) on a side away from the measurement structure main body (5), and the outlet flange (6) is provided with a docking boss (20) on a side away from the measurement structure main body (5).

9. The non-contact measurement structure for an aircraft engine combustion chamber outlet according to claim 1, characterized in that: The optical glass lens (11) is an optical quartz glass lens of model JGS2, and the optical glass lens (11) has a diameter of 64 mm, a thickness of 35 mm, and a pressure resistance of ≥3.0 MPa.

10. The non-contact measurement structure for an aircraft engine combustion chamber outlet according to claim 1, characterized in that: The outlet water pipe (2), the inlet water pipe (7) and the cooling air pipe (17) all have a diameter of 10 mm.

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