Comprehensive optical measurement platform for main combustion chamber of aero-engine

Abstract

The utility model discloses a comprehensive optical measurement platform for a main combustion chamber of an aero-engine, which belongs to the technical field of aero-engines and comprises a workbench, and a supporting mechanism is arranged at the top of the workbench. According to the utility model, the engine test sections with different sizes are placed on the supporting plate, the diffuser and the air outlet square-to-round section which are matched with the end parts of the engine test sections are respectively arranged at the two ends of the engine test sections, and the height of the equal-straight pressure stabilizing section can be adjusted through the first electric push rod. The height of the three-way joint can be adjusted through a second electric push rod, so that the end part of the equal-straight pressure stabilizing section is aligned with the end part of the diffuser, and the end part of the air outlet square-to-round section is aligned with the end part of the three-way joint, so that engine test sections with different sizes can be connected and mounted; comprehensive optical measurement of engine test sections of different sizes is realized, and the practicability is good.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of aero-engine, more particularly to a comprehensive optical measuring platform of aero-engine main combustion chamber. BACKGROUND

[0002] The aero-engine is a kind of highly complex and precision thermodynamic machinery, as the heart of aircraft, not only the power of aircraft flight, also is the important driving force for promoting the development of aviation industry. When aircraft flies in the air, the air in the environment enters the compressor through the air inlet and is changed into high-pressure high-speed airflow, and then mixes with the injected fuel in the combustion chamber and burns, generates a large amount of high-temperature gas, and drives the turbine to rotate to do work, and then sprays to the rear, to provide the power for the aircraft to soar in the blue sky. In the aero-engine, the temperature of the combustion chamber is the highest, the airflow is complex, and the working environment is extremely harsh, so the parameters inside it need to be measured.

[0003] After searching, the invention patent with publication number CN104764609A discloses a kind of comprehensive optical measuring platform of aero-engine main combustion chamber, adopts multiple optical measurement means, carries out comprehensive measurement to the parameter inside the combustion chamber of aero-engine, air flow enters isodiametric steady pressure section by air inlet circle conversion square section, combustion experiment section is fixedly installed between diffuser and outlet square conversion circle section, air flow enters combustion experiment section by diffuser deceleration expansion, glass observation window for optical measurement is embedded in the two sides of combustion experiment section;In cold state experiment, airflow flows out from the combustion chamber outlet of single head portion rectangular experimental piece and enters cold flow tee, the main road outlet is closed, and the airflow flows out from bypass, for high-temperature pure air flow, based on combustion experiment equipment, single head portion experimental piece is taken, can carry out kerosene atomization, speed, temperature and component measurement in combustion chamber, complete aero-engine combustion chamber flow field test experiment, realize the fine measurement of aero-engine combustion flow field. But the above-mentioned patent still has the following deficiencies: it is inconvenient to support the air inlet circle conversion square isodiametric steady pressure section, cold flow tee and other structures for testing the aero-engine main combustion chamber, and it is inconvenient to adjust the height position of the air inlet circle conversion square, isodiametric steady pressure section, cold flow tee and other structures according to the size change of the aero-engine main combustion chamber, which affects the connection and installation of the aero-engine main combustion chamber, and further affects the test of the aero-engine main combustion chamber, therefore we propose a kind of comprehensive optical measuring platform of aero-engine main combustion chamber. UTILITY MODEL CONTENT

[0004] In view of the problems in the prior art, the utility model aims at providing a comprehensive optical measuring platform of aero-engine main combustion chamber.

[0005] To solve the above problems, the utility model adopts the following technical scheme:

[0006] The utility model provides an integrated optical measuring platform of aeroengine main combustion chamber, including work table, the top of work table is provided with support mechanism, the top of support mechanism places engine test section, one end of work table is fixedly installed with a plurality of first electric push rods, and the output of a plurality of first electric push rods all extends to the top of work table and is fixedly connected with equal straight voltage stabilizing section, one end of equal straight voltage stabilizing section is installed with air inlet round conversion square section, the other end of air inlet round conversion square section is installed with diffuser, one end of diffuser and one end of engine test section are connected, the other end of work table is fixedly installed with a plurality of second electric push rods, and the output of a plurality of second electric push rods extends to the top of work table and is fixedly connected with tee joint, one end of tee joint is installed with air outlet square conversion round section, and the end of air outlet square conversion round section and the other end of engine test section are connected, the other end of tee joint is fixedly installed with first switch valve, and the end of first switch valve is provided with cooling mechanism, the third end of tee joint is fixedly installed with second switch valve.

[0007] As a preferred scheme of the utility model, the support mechanism includes two groups of support columns fixedly connected to the top surface of the work table, and the top ends of the two groups of support columns are fixedly connected with support plates.

[0008] As a preferred scheme of the utility model, the cooling mechanism includes heat exchange pipes fixedly installed at the end of the first switch valve, a heat exchange cylinder is fixedly sleeved to the outside of the heat exchange pipes, a water inlet pipe is fixedly sleeved to one side of the heat exchange cylinder, and a water return pipe is fixedly sleeved to the other side of the heat exchange cylinder.

[0009] As a preferred scheme of the utility model, the control panel is fixedly installed on the side surface of the work table and is electrically connected with the first electric push rods and the second electric push rods.

[0010] As a preferred scheme of the utility model, a plurality of support legs are fixedly connected to the bottom surface of the work table, and anti-skid blocks are fixedly connected to the bottom ends of the plurality of support legs.

[0011] As a preferred scheme of the utility model, the engine test section is placed on the top surface of the support plate.

[0012] Compared with the prior art, the utility model has the advantages that:

[0013] The utility model discloses a support mechanism, first electric push rod, equal straight pressure section, air inlet round square section, diffuser, three -way joint, first switch valve, second switch valve and cooling mechanism are arranged on the workbench, and the equal straight pressure section is connected with the air inlet round square section, and the diffuser is connected with the three -way joint, and the first switch valve is connected with the air inlet round square section, and the second switch valve is connected with the three -way joint, and the cooling mechanism is connected with the diffuser. BRIEF DESCRIPTION OF DRAWINGS

[0014] Figure 1 It is the whole structure schematic diagram of the utility model;

[0015] Figure 2 It is the structure schematic diagram of the utility model workbench;

[0016] Figure 3 It is the structure schematic diagram of the utility model equal straight pressure section;

[0017] Figure 4 It is the structure schematic diagram of the utility model cooling mechanism.

[0018] Mark explanation in drawing:

[0019] 1, workbench;2, support mechanism;3, engine test section;4, first electric push rod;5, equal straight pressure section;6, air inlet round square section;7, diffuser;8, three -way joint;9, first switch valve;10, second switch valve;11, cooling mechanism;12, second electric push rod;13, air outlet square round section;14, support column;15, support plate;16, heat exchange pipe;17, heat exchange cylinder;18, water inlet pipe;19, backwater pipe;20, support leg;21, antiskid block;22, control panel. DETAILED DESCRIPTION

[0020] The technical schemes in the embodiments of the utility model will be described clearly and completely below in conjunction with the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all the embodiments, and all other embodiments obtained by the ordinary skilled in the art without creative work on the basis of the embodiments in the utility model belong to the scope of protection of the utility model.

[0021] In the description of the utility model, it needs to explain, the term "upper", "lower", "internal", "external", "top / bottom end" and so on indicate the orientation or position relation is based on the orientation or position relation shown in the drawing, only for the convenience of describing the utility model and simplifying the description, and not indicate or imply that the device or element must have a particular orientation, construct and operate with a particular orientation, therefore cannot be understood as the limitation of the utility model. In addition, the term "first", "second" is only for the purpose of description, and cannot be understood as indicating or implying relative importance.

[0022] In the description of the utility model, it needs to explain, unless otherwise expressly provided and limited, the terms "mounting", "setting", "sleeving / interfacing", "connecting" and so on should be understood broadly, for example, "connecting", can be fixed connection, can also be detachable connection, or integrally connected, can be mechanical connection, can also be electrical connection, can be directly connected, can also be indirectly connected through intermediate medium, can be the communication inside two elements. For ordinary skilled in the art, the specific meaning of the above terms in the utility model can be understood according to the specific circumstances.

[0023] Embodiment:

[0024] Please refer to Figures 1-4 , a comprehensive optical measurement platform of aero-engine main combustion chamber, including workbench 1, the top of workbench 1 is provided with support mechanism 2, the top of support mechanism 2 is placed with engine test section 3, one end of workbench 1 is fixedly installed with a plurality of first electric push rods 4, the output end of a plurality of first electric push rods 4 extends to the top of workbench 1 and is fixedly connected with equal straight pressure stabilizing section 5, one end of equal straight pressure stabilizing section 5 is installed with inlet circular conversion square section 6, the other end of inlet circular conversion square section 6 is installed with diffuser 7, one end of diffuser 7 is connected with one end of engine test section 3, the other end of workbench 1 is fixedly installed with a plurality of second electric push rods 12, the output end of a plurality of second electric push rods 12 extends to the top of workbench 1 and is fixedly connected with tee joint 8, one end of tee joint 8 is installed with outlet square conversion circular section 13, the end of outlet square conversion circular section 13 is connected with the other end of engine test section 3, the other end of tee joint 8 is fixedly installed with first switch valve 9, the end of first switch valve 9 is provided with cooling mechanism 11, the third end of tee joint 8 is fixedly installed with second switch valve 10.

[0025] In the embodiment, the optical measurement system of the prior art is used to measure the situation in the engine test section 3.

[0026] Specifically, please refer to Figure 1 and Figure 2 , support mechanism 2 includes two groups of support columns 14 fixedly connected on the top surface of workbench 1, and the top ends of the two groups of support columns 14 are fixedly connected with a support plate 15.

[0027] Specifically, please refer to Figure 1 , Figure 3 and Figure 4 , the cooling mechanism 11 comprises a heat exchange pipe 16 fixedly installed at the end of the first switch valve 9, the outer side of the heat exchange pipe 16 is fixedly sleeved with a heat exchange cylinder 17, one side of the heat exchange cylinder 17 is fixedly sleeved with a water inlet pipe 18, and the other side of the heat exchange cylinder 17 is fixedly sleeved with a water return pipe 19.

[0028] In the embodiment, the end of the water inlet pipe 18 is connected with a water pump and a water pool, so as to guide the cooling water into the inner cavity of the heat exchange cylinder 17, and guide the cooling water in the heat exchange cylinder 17 back to the water pool through the water return pipe 19.

[0029] Specifically, please refer to Figure 1 , the side of the workbench 1 is fixedly installed with a control panel 22, and the control panel 22 is electrically connected with the first electric push rod 4 and the second electric push rod 12 respectively.

[0030] In the embodiment, the first electric push rod 4 and the second electric push rod 12 are controlled by the control panel 22.

[0031] Specifically, please refer to Figure 1 , the bottom surface of the workbench 1 is fixedly connected with a plurality of supporting legs 20, and the bottom end of the plurality of supporting legs 20 is fixedly connected with anti-skid blocks 21.

[0032] In the embodiment, the workbench 1 is supported by the supporting legs 20 and the anti-skid blocks 21.

[0033] Specifically, please refer to Figures 1 to 3 , the engine test section 3 is placed on the top surface of the supporting plate 15.

[0034] In the embodiment, the engine test section 3 is supported by the supporting column 14 and the supporting plate 15.

[0035] Working principle: in use, first, the engine test section 3 to be tested is placed on the support plate 15, and the diffuser 7 and the outlet gas square-to-round section 13 are respectively installed at both ends of the support plate 15 and adapt to the end of the support plate 15, then the first electric push rod 4 is started to drive the straight steady pressure section 5 and the inlet gas round-to-square section 6 to move up and down, so that the end of the straight steady pressure section 5 is aligned with the end of the diffuser 7, and one end of the diffuser 7 and the end of the straight steady pressure section 5 are connected through bolts, then the second electric push rod 12 is started to drive the three-way joint 8, the first switch valve 9, the second switch valve 10 and the cooling mechanism 11 to move up and down, so that the end of the outlet gas square-to-round section 13 is aligned with the end of the three-way joint 8, and the end of the outlet gas square-to-round section 13 and the end of the three-way joint 8 are connected through bolts, finally, the incoming air is directly introduced into the air distribution platform after passing through the filter, the required incoming flow condition is obtained, the air flow is uniformly distributed through the mixer, the incoming air enters the mixer at the outlet of the heater after passing through the heater, the air passing through different heaters is mixed and uniformly distributed again, the incoming air enters the inlet gas round-to-square section 6, and the air enters the engine test section 3 through the straight steady pressure section 5 and the diffuser 7, and the optical measurement system is used to measure the experimental model, and the measurement is completed.

[0036] The above merely describes a preferred specific implementation manner of the present application, but the protection scope of the present application is not limited to this, any skilled person in the art can make equivalent replacement or change according to the technical scheme and improvement concept of the present application within the technical range disclosed by the present application, which should be covered in the protection scope of the present application.

Claims

1. An integrated optical measurement platform for aeroengine main combustion chamber, comprising a workbench (1), characterized in that: The top of the workbench (1) is provided with a support mechanism (2), the top of the support mechanism (2) is placed with an engine test section (3), one end of the workbench (1) is fixedly installed with a plurality of first electric push rods (4), the output ends of the plurality of first electric push rods (4) are extended to the top of the workbench (1) and are fixedly connected with an equal straight pressure stabilizing section (5), one end of the equal straight pressure stabilizing section (5) is installed with an air inlet circular-to-square section (6), the other end of the air inlet circular-to-square section (6) is installed with a diffuser (7), one end of the diffuser (7) is connected with one end of the engine test section (3), the other end of the workbench (1) is fixedly installed with a plurality of second electric push rods (12), the output ends of the plurality of second electric push rods (12) are extended to the top of the workbench (1) and are fixedly connected with a tee joint (8), one end of the tee joint (8) is installed with an air outlet square-to-circular section (13), the end of the air outlet square-to-circular section (13) is connected with the other end of the engine test section (3), the other end of the tee joint (8) is fixedly installed with a first on-off valve (9), the end of the first on-off valve (9) is provided with a cooling mechanism (11), the third end of the tee joint (8) is fixedly installed with a second on-off valve (10).

2. The integrated optical measurement platform for a main combustion chamber of an aeroengine according to claim 1, characterized in that: The support mechanism (2) comprises two groups of support columns (14) fixedly connected to the top surface of the workbench (1), and the top ends of the two groups of support columns (14) are fixedly connected with support plates (15).

3. The integrated optical measurement platform for a main combustion chamber of an aeroengine according to claim 1, characterized in that: The cooling mechanism (11) comprises a heat exchange pipe (16) fixedly installed at the end of the first on-off valve (9), the outer side of the heat exchange pipe (16) is fixedly sleeved with a heat exchange cylinder (17), one side of the heat exchange cylinder (17) is fixedly sleeved with a water inlet pipe (18), and the other side of the heat exchange cylinder (17) is fixedly sleeved with a backwater pipe (19).

4. The integrated optical measurement platform for a main combustion chamber of an aeroengine according to claim 1, characterized in that: A control panel (22) is fixedly installed on the side surface of the workbench (1), and the control panel (22) is electrically connected with the first electric push rods (4) and the second electric push rods (12) respectively.

5. The integrated optical measurement platform for a main combustion chamber of an aeroengine according to claim 1, characterized in that: A plurality of support legs (20) are fixedly connected to the bottom surface of the workbench (1), and the bottom ends of the plurality of support legs (20) are fixedly connected with anti-skid blocks (21).

6. The integrated optical measurement platform for a main combustion chamber of an aeroengine according to claim 2, characterized in that: The engine test section (3) is placed on the top surface of the support plate (15).

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