CN210720301U

CN210720301U - Aeroengine fuel combustion characteristic experiment table

Info

Publication number: CN210720301U
Application number: CN201921428710.9U
Authority: CN
Inventors: 汪小憨; 王宁; 杨卫斌
Original assignee: Guangzhou Institute of Energy Conversion of CAS
Current assignee: Guangzhou Institute of Energy Conversion of CAS
Priority date: 2019-08-29
Filing date: 2019-08-29
Publication date: 2020-06-09
Anticipated expiration: 2029-08-29

Abstract

The utility model discloses an aeroengine fuel combustion characteristic laboratory bench, including base and machine casket, be equipped with air intake duct and combustion chamber in the machine casket, the one end of air intake duct is connected on the base, the other end is connected with the combustion chamber, the exhanst gas outlet of combustion chamber is connected to the top of machine casket, fuel inlet and main wind air intake of burning have been seted up to the one end that the air intake duct is connected on the base, the position of being connected with the air intake duct in the combustion chamber is equipped with the ignition bar, be equipped with a plurality of cooling air intake on the machine casket, still be provided with the monitoring subassembly on the machine casket, the monitoring subassembly is used for observing the inside condition of combustion chamber and installs the equipment of collecting. The utility model discloses can cover whole aeroengine's operating condition, the firing and the burning characteristic of fuel are shown comprehensively, and add simultaneously on the test bench and be equipped with observation window and internal thread through-hole to the various data acquisition instrument of adaptation gather inside burning data, overall structure is simple and easy, and the cost is lower, and is easy and simple to handle.

Description

Aeroengine fuel combustion characteristic experiment table

Technical Field

The utility model relates to an engineering thermophysics and combustion technology technical field, concretely relates to aeroengine fuel combustion characteristic laboratory bench.

Background

As the aviation industry develops, the requirements for the combustion performance of aviation engine fuel are increased, and it is necessary to study the ignition and combustion characteristics of aviation fuel. Some existing technologies can detect the ignition and combustion characteristics of fuel, for example, a fast press, a shock tube and other experimental devices can be used for measuring the ignition delay of the fuel, and a laminar flame velocity of the fuel can be measured by using a laminar flame impingement experimental device, but these detection methods cannot consider the influence of turbulence on the ignition and combustion characteristics of the fuel, cannot cover the actual working conditions of the aircraft engine, the difference between the detection result and the ignition and combustion characteristics of the fuel under the actual working conditions of the aircraft engine is large, and the obtained data are not matched with the actual working conditions and can only be used as reference.

On the other hand, the experimental device which can cover the actual working condition of the aero-engine at present, such as an aero-engine stand, has some defects. The aeroengine rack is large in size, high in manufacturing cost, less in experimental data which can be obtained, insufficient in experimental research, and insufficient in requirement for detecting ignition and combustion characteristics of fuel under the actual working condition of the aeroengine. Therefore, a comprehensive experiment detection table which is simple and easy to implement, has low cost, has a real aircraft engine combustion head, can cover the actual working condition of the aircraft engine, and can acquire enough data to detect the ignition and combustion characteristics of the aircraft fuel is urgently needed.

SUMMERY OF THE UTILITY MODEL

To the not enough of prior art, the utility model provides an aeroengine fuel combustion characteristic laboratory bench.

In order to achieve the above purpose, the technical scheme of the utility model is that:

the utility model provides an aeroengine fuel combustion characteristic laboratory bench, includes base and machine casket, be equipped with air intake duct and combustion chamber in the machine casket, air intake duct's one end is connected on the base, and the other end is connected with the combustion chamber, the exhanst gas outlet of combustion chamber is connected to the top of machine casket, fuel inlet and main burning wind air intake have been seted up to air intake duct one end of connecting on the base, the position of being connected with air intake duct in the combustion chamber is equipped with the ignition bar, be equipped with a plurality of cooling air intake on the machine casket, still be provided with the monitoring subassembly on the machine casket, the monitoring subassembly is used for observing the equipment that the data was collected in the interior condition of combustion chamber and installation.

Further, the casing comprises a casing upper portion and a casing lower portion, the casing upper portion and the casing lower portion are both of a cylinder structure, the casing upper portion is connected with the casing lower portion in a sealing mode, an air inlet channel in the casing lower portion and a space outside the combustion chamber form an outer cavity, and a smoke outlet of the combustion chamber is connected to the top end of the casing upper portion.

Further, the combustion chamber includes the quartz capsule, the both ends of quartz capsule are provided with quartz capsule draw-in groove and quartz capsule draw-in groove down respectively, it is used for blocking the quartz capsule and makes the sealed draw-in groove in both ends of quartz capsule to be equipped with on quartz capsule draw-in groove and the quartz capsule draw-in groove down, it is equipped with the fastener that is used for pressing from both sides tight quartz capsule to go up the quartz capsule draw-in groove and be equipped with down on the quartz capsule draw-in groove.

Further, the barrel on machine casket upper portion stretches into partly in the machine casket lower part, it is connected with the barrel on machine casket upper portion to go up the quartz capsule draw-in groove, and the junction is network structure, the quartz capsule draw-in groove is connected with the air intake duct down, the one end and the air intake duct intercommunication of quartz capsule, the other end are connected with the flue gas pipeline, flue gas pipeline and quartz capsule intercommunication to set up in machine casket upper portion, extend to the top on machine casket upper portion.

Furthermore, the flue gas pipeline is of a multi-section reducing cylinder structure.

Further, the monitoring assembly comprises a plurality of internally threaded through holes and observation windows which are arranged on the casing and used for mounting the thermocouples or the sensors.

Furthermore, the observation window comprises a short branch pipe extending out of the middle part of the lower part of the casing along the radial direction of the casing, and a glass window is fixed at the end part of the short branch pipe through a flange.

Furthermore, a perforated clamping sleeve male connector used for sealing the inner space of the casing is arranged on the inner thread through hole.

Furthermore, the top of the casing is connected with an exhaust branch pipe, and a pressure control valve is installed on the exhaust branch pipe.

Furthermore, a lifting support is arranged on the base.

Compared with the prior art, the utility model, have following advantage:

1. the combustion under a turbulent flow state can be realized, and the ignition and combustion characteristics of the obtained fuel contain the influence of the turbulent flow and are closer to the actual condition;

2. the actual working conditions of all aero-engines can be covered, and the ignition and combustion characteristics of the fuel can be comprehensively shown;

3. the method is simple and easy to implement, low in cost and convenient to operate;

4. the device is provided with a real aircraft engine combustion head, and the detected ignition and combustion characteristics of the fuel are real and reliable;

5. the lifting support is arranged at the bottom of the experiment table, and can be adjusted according to different detection equipment so as to detect and record combustion field information and flame forms at different height positions, so that the detection equipment can operate quickly and effectively;

synthesize above-mentioned several points, the utility model discloses can cover whole aeroengine's operating condition, the firing and the burning characteristic of fuel are shown comprehensively, and add the internal thread through-hole that is equipped with the observation window that is used for observing the combustion chamber internal conditions simultaneously on the test bench and is used for installing thermocouple or sensor to the various data acquisition instrument of adaptation gathers inside burning data, overall structure is simple and easy, and the cost is lower, easy and simple to handle.

Drawings

FIG. 1 is a schematic structural diagram of an aircraft engine fuel combustion characteristic test bench;

FIG. 2 is a schematic structural diagram of an aircraft engine fuel combustion characteristic experiment table;

FIG. 3 is a schematic structural diagram of an aircraft engine fuel combustion characteristic experiment table;

description of reference numerals: 1. a case; 11. the upper part of the casing; 12. the lower part of the casing; 121. a fuel inlet; 122. a main combustion air inlet; 123. a primary cooling air inlet; 124. a secondary cooling air inlet; 3. an exhaust branch pipe; 4. an air intake; 41. a cyclone wind baffle plate; 5. a combustion chamber; 51. an upper quartz tube clamping groove; 52. a lower quartz tube clamping groove; 53. a quartz tube; 54. a fastener; 6. a flue gas duct; 61. a vent hole; 7. an observation window; 8. an internally threaded through bore; 9. a base.

Detailed Description

In order to make the above objects, features and advantages of the present invention more comprehensible, the present invention is described in detail with reference to the accompanying drawings and the detailed description.

Examples

As shown in FIG. 1, an aeroengine fuel combustion characteristic experiment table, a base 9, a casing 1 and an exhaust branch pipe 3, wherein the casing 1 comprises a casing upper part 11 and a casing lower part 12, both the casing upper part 11 and the casing lower part 12 are of a cylinder structure, the bottom of the casing upper part 11 is hermetically connected with the top of the casing lower part 12, the exhaust branch pipe 3 is connected with the tail end of the casing upper part 11 and is provided with a pressure control valve, an air inlet passage 4 and a combustion chamber 5 are arranged in the casing lower part 12, the combustion chamber 5 extends into the casing upper part 11, one end of the air inlet passage 4 is connected with the base 9, the other end is connected with the combustion chamber 5, one end of the air inlet passage 4 connected with the base 9 is provided with a fuel inlet 121 and a main combustion air inlet 122, a portion connected with the air inlet passage 4 in the combustion chamber 5 is provided with an ignition rod, a space except for the air inlet passage 4 and the combustion, and a plurality of cooling air inlets are arranged on the lower part 12 of the casing.

As shown in fig. 1 and fig. 2, the air intake duct 4 and the combustion chamber 5 are both of a cylindrical structure and are coaxially arranged with the casing 1, a fuel inlet 121 is arranged at one end of the air intake duct 4 connected with the base 9, a main combustion air inlet 122 is arranged on the side surface of the air intake duct 4, 2 main combustion air inlets 122 are uniformly distributed on the side surface of the air intake duct 4, and a swirl air baffle 41 is further arranged at one end of the air intake duct 4 connected with the combustion chamber 5, so that an inner-outer double-layer swirl air structure is formed. The combustion chamber 5 is composed of a quartz tube 53, two ends of the quartz tube 53 are respectively provided with an upper quartz tube clamping groove 51 and a lower quartz tube clamping groove 52, clamping grooves used for clamping the quartz tube 53 and sealing two ends of the quartz tube 53 are respectively arranged on the upper quartz tube clamping groove 51 and the lower quartz tube clamping groove 52, a fastening piece 54 used for clamping the quartz tube 53 is further additionally arranged on the upper quartz tube clamping groove 51 and the lower quartz tube clamping groove 52, the fastening piece 54 is a part capable of adjusting the length of the fastening piece so as to install the quartz tube 53, a screw rod and a nut are adopted to tightly abut against the fastening piece in the embodiment, so that the upper quartz tube clamping groove 51 and the lower quartz tube clamping groove 52 can tightly abut against the quartz tube 53, and the quartz tube is kept sealed.

As shown in fig. 2 and 3, the diameter of the casing upper portion 11 is smaller than that of the casing lower portion 12, the barrel of the casing upper portion 11 extends into a part of the casing lower portion 12, the upper quartz tube clamping groove 51 is connected with the end of the barrel of the casing upper portion 11 extending into the casing lower portion 12, and the end of the barrel of the casing upper portion 11 extending into the casing lower portion 12 is of a cylindrical net structure, so that the cooling air can be blown into and mixed with the flue gas while communicating the outer cavity spaces of the casing upper portion 11 and the casing lower portion 12. Lower quartz capsule draw-in groove 52 is connected with air intake duct 4, quartz capsule 53's one end and air intake duct 4 intercommunication, and be equipped with the ignition rod, the other end is connected with flue gas pipeline 6, flue gas pipeline 6 and quartz capsule 53 intercommunication, and coaxial setting is in casket upper portion 11, discharge flue gas to exhaust branch 3 department, and flue gas pipeline 6's structure is the reducing cylinder structure of multistage, and bottom portion is equipped with air vent 61 in the below of reducing cylinder structure, set up like this, when letting in the cooling air, can effectively carry out ventilation cooling to flue gas pipeline 6 inside through its reducing part.

As shown in fig. 1, the lower portion 12 of the casing is further provided with a plurality of observation windows 7 for data acquisition and data detection, the number of the observation windows 7 is four, the observation windows 7 are uniformly distributed along the circumferential direction of the lower portion 12 of the casing, the observation windows 7 are specifically structured as short branch pipes extending from the middle portion of the lower portion 12 of the casing along the radial direction thereof, and the end portions of the short branch pipes are fixed with glass windows through flanges. The casing 1 is provided with a plurality of internal thread through holes 8 for installing thermocouples or sensors, and the internal thread through holes 8 are provided with perforated cutting sleeve external thread joints for sealing the internal space of the casing 1 so as to ensure the sealing performance of the internal space of the casing 1. The cooling air inlet comprises a primary cooling air inlet 123 and a secondary cooling air inlet 124, 2 primary cooling air inlets 123 are arranged on the base 9, and the primary cooling air inlets 123 can output different air volumes of gas according to actual requirements, such as outputting cooling air or outputting cleaning gas near the observation window 7; the secondary cooling air inlet 124 is arranged at the top position of the lower part 12 of the casing and at the position near the position connected with the upper part 11 of the casing, and is used for cooling the flue gas pipeline 6 and the outlet part of the combustion chamber 5.

Specifically, the positions of the internal thread through holes 8 are arranged on the outer wall of the lower part 12 of the casing and the outer wall of the upper part 11 of the casing between every two observation windows 7, two rows of internal thread through holes 8 are symmetrically arranged on the outer wall of the middle lower section of the upper part 11 of the casing along the axial direction, a plurality of centrosymmetric internal thread through holes 8 are also arranged on the upper section of the upper part 11 of the casing, and the internal thread through holes 8 are also arranged on the same positions corresponding to the smoke pipeline 6 inside the upper part 11 of the casing so that the sensor can extend into the internal thread through holes 8 to detect corresponding data. Meanwhile, the base 9 can be provided with a lifting support, and the coordinate position of the observation window 7 can be adjusted according to needs to be matched with a data sampling and detecting system to carry out data acquisition and analysis on the internal combustion condition.

Specifically, when in use, firstly, the gas and the main combustion air enter the air intake duct 4 through the main combustion air inlet 122 and the fuel inlet 121 arranged on the lower part 12 of the casing and the base 9, the main combustion air forms double-layer swirling air through the swirling air baffle 41 inside the air intake duct 4 and is mixed with the gas, the mixed main combustion air and gas mixture enters the combustion chamber 5 after passing through the air intake duct 4, and then the mixture is ignited by electric sparks generated by the ignition bar, so that the mixture is fully combusted in the combustion chamber 5. And finally, the flue gas after the mixture is combusted circulates to the exhaust branch pipe 3 through the flue gas pipeline 6, and is cooled by combining with cooling air through the through hole on the reducing cylinder structure of the flue gas pipeline 6, and then is further discharged from the exhaust branch pipe 3.

When the experiment table is used for carrying out combustion characteristic experiments on fuel, the internal combustion condition of the equipment for observing and sampling data can be sampled through the internal thread through hole 8 and the observation window 7 on the experiment table, so that the standard parameters for detecting the ignition and combustion characteristics of aviation fuel are supplemented.

The above embodiments are only for illustrating the technical concept and features of the present invention, and the purpose thereof is to enable those skilled in the art to understand the contents of the present invention and to implement the present invention, which cannot limit the protection scope of the present invention. All equivalent changes and modifications made according to the spirit of the present invention should be covered by the protection scope of the present invention.

Claims

1. An aeroengine fuel combustion characteristic laboratory bench which characterized in that: including base (9) and machine casket (1), be equipped with air intake duct (34) and combustion chamber (5) in machine casket (1), the one end of air intake duct (34) is connected on base (9), and the other end is connected with combustion chamber (5), the exhanst gas outlet of combustion chamber (5) is connected to the top of machine casket (1), fuel inlet (121) and main burning wind air intake (122) have been seted up to the one end that air intake duct (34) were connected on base (9), the position of being connected with air intake duct (34) in combustion chamber (5) is equipped with the ignition stick, be equipped with a plurality of cooling air intake on machine casket (1), still be provided with the monitoring subassembly on machine casket (1), the monitoring subassembly is used for observing combustion chamber (5) internal conditions and the equipment of installation collection data usefulness.

2. The aircraft engine fuel combustion characteristic test stand of claim 1, wherein: the engine case (1) comprises an upper engine case part (11) and a lower engine case part (12), wherein the upper engine case part (11) and the lower engine case part (12) are both of a cylinder structure, the upper engine case part (11) is in sealing connection with the lower engine case part (12), an air inlet channel (34) in the lower engine case part (12) and a space outside a combustion chamber (5) form an outer cavity, and a smoke outlet of the combustion chamber (5) is connected to the top end of the upper engine case part (11).

3. The aircraft engine fuel combustion characteristic test stand of claim 2, wherein: the combustion chamber (5) comprises a quartz tube (53), the two ends of the quartz tube (53) are respectively provided with a quartz tube clamping groove (51) and a lower quartz tube clamping groove (52), clamping grooves used for clamping the quartz tube (53) and sealing the two ends of the quartz tube (53) are arranged on the upper quartz tube clamping groove (51) and the lower quartz tube clamping groove (52), and fasteners (54) used for clamping the quartz tube (53) are arranged on the upper quartz tube clamping groove (51) and the lower quartz tube clamping groove (52).

4. The aircraft engine fuel combustion characteristic test stand of claim 3, wherein: the barrel of machine casket upper portion (11) stretches into partly in machine casket lower part (12), go up quartz capsule draw-in groove (51) and be connected with the barrel of machine casket upper portion (11), the junction is network structure, quartz capsule draw-in groove (52) are connected with air intake (34) down, the one end and air intake (34) intercommunication of quartz capsule (53), the other end are connected with flue gas pipeline (6), flue gas pipeline (6) and quartz capsule (53) intercommunication to set up in machine casket upper portion (11), extend to the top of machine casket upper portion (11).

5. The aircraft engine fuel combustion characteristic test stand of claim 4, wherein: the flue gas pipeline (6) is of a multi-section reducing cylinder structure.

6. The aircraft engine fuel combustion characteristic test stand of claim 1, wherein: the monitoring assembly comprises a plurality of internal thread through holes (8) and observation windows (7), wherein the internal thread through holes are formed in the casing (1) and used for mounting thermocouples or sensors.

7. The aircraft engine fuel combustion characteristic test stand of claim 6, wherein: the observation window (7) comprises a short branch pipe extending out of the middle of the lower part (12) of the casing along the radial direction of the observation window (7), and a glass window is fixed at the end part of the short branch pipe through a flange.

8. The aircraft engine fuel combustion characteristic test stand of claim 6, wherein: and the inner thread through hole (8) is provided with a perforating clamping sleeve outer thread joint for sealing the inner space of the casing (1).

9. The aircraft engine fuel combustion characteristic test stand of claim 1, wherein: the top of the casing (1) is connected with an exhaust branch pipe (3), and a pressure control valve is installed on the exhaust branch pipe (3).

10. The aircraft engine fuel combustion characteristic test stand of claim 1, wherein: and a lifting support is arranged on the base (9).