CN210426968U - Microminiature aviation turbine engine oil spout ring flow test system - Google Patents
Microminiature aviation turbine engine oil spout ring flow test system Download PDFInfo
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- CN210426968U CN210426968U CN201920997529.3U CN201920997529U CN210426968U CN 210426968 U CN210426968 U CN 210426968U CN 201920997529 U CN201920997529 U CN 201920997529U CN 210426968 U CN210426968 U CN 210426968U
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Abstract
The utility model discloses a microminiature aviation turbine engine oil spout ring flow test system, which comprises an oil spout ring part, a fuel tank part, a pressure measurement adjusting part and a collecting device; the method is characterized in that: the oil injection ring component comprises an oil inlet pipe, a ring body and an oil injection needle; the fuel tank component comprises an engine fuel tank, an engine fuel oil filter and an engine oil pump; the pressure measuring component comprises a pressure regulator, a pressure regulating capillary tube (S1), a pressure display and a pressure capillary tube (S2); the utility model has the advantages that: the mass flow of fuel at the outlet of each fuel injection needle of the fuel injection ring of each microminiature aircraft turbine engine can be measured through a flow measuring system, so that whether the fuel flow at the outlet of each fuel injection needle is uniform or not is verified; secondly, the pressure regulator adopts a stepless speed and pressure regulator, so that the fuel flow at the outlet of each fuel injection needle can be measured under the condition of different inlet total pressures through more accurate adjustment; thirdly, the system is comprehensive, good in reliability, good in economic performance and simple in structure.
Description
Technical Field
The utility model relates to a microminiature aviation turbine engine technical field especially relates to microminiature aviation turbine engine oil spout circulation test system.
Technical Field
The microminiature aviation turbine engine can be divided into a micro turbine engine and a small turbine engine, the limit of the micro turbine engine and the small turbine engine is that the thrust is 100daN, and the indexes for evaluating the performance of the micro turbine engine mainly comprise: thrust, unit thrust, oil consumption rate and total efficiency, thrust-weight ratio and the like; the working principle of the microminiature aviation turbine engine is that an external power supply drives a starting motor, the starting motor drives a centrifugal compressor to rotate, meanwhile, a fuel pump presses fuel oil into a fuel injection ring from an oil tank at high speed and high pressure, then the fuel oil is injected to an evaporation pipe at high speed through fuel injection needles which are distributed on a ring body at equal intervals, and the fuel oil is evaporated and atomized in the evaporation pipe rapidly. The fuel oil and the air in the combustion chamber are quickly and uniformly mixed, the temperature is quickly raised through a hot fire head of an igniter to ignite the oil-gas mixture, the fuel oil-gas mixture is quickly combusted and expanded, the ultra-high temperature and high pressure gas generated after combustion flows to a next stage of turbine to drive the turbine to rotate at high speed to apply work, finally the ultra-high temperature and high pressure gas flows out through a tail nozzle, and the thrust is generated through the sprayed high-speed airflow; the microminiature aviation turbine engine has the advantages of precise structure, small volume, large thrust-weight ratio, high combustion efficiency and the like, is mainly used for providing required power for unmanned aerial vehicles, flying missiles, target drone, light airplanes or personal aircrafts and the like, and can also provide power and the like for ground devices.
The fuel system of the microminiature aviation turbine engine is of great importance as compared with the blood vessel in the human body; the aircraft plays an important role in ensuring stable, reliable and normal operation of the aircraft under the conditions of starting, climbing, emergency maneuvering and the like. The uniformity of the oil injection annular flow of the microminiature aircraft turbine engine is related to the combustion work of the whole microminiature aircraft turbine engine combustion chamber, the uniformity of the oil injection quantity of an oil injection needle determines the uniformity of a temperature field during combustion, the uniformity of the oil injection quantity also influences the service life of a next stage turbine, the combustion efficiency of the combustion chamber can be influenced under the conditions of local rich oil or lean oil and the like, particularly, the turbine blades can be burnt and damaged under the condition of rich oil, and the service life of the turbine structure is shortened; it is therefore necessary to perform a flow test on the spray ring structure.
The utility model provides a microminiature aviation turbine engine oil spout ring flow test system, this test system can discover effectively that the inhomogeneous problem of oil spout that microminiature aviation turbine engine oil spout ring appears, especially to establishing the basis for the inside flow field of oil spout ring of study and making the analysis in the future, provide the reference suggestion for the design of microminiature aviation turbine engine in future; the mass flow of fuel at the outlet of each fuel injection needle of the fuel injection ring of each microminiature aviation turbine engine can be measured through the flow testing system, so that whether the fuel flow at the outlet of each fuel injection needle is uniform or not is verified; the pressure regulator adopts a stepless speed-regulating pressure regulator, so that the fuel flow at the outlet of each fuel injection needle can be more accurately measured under the condition of different inlet total pressures; the flow testing system can ensure that various microminiature aviation turbine engines play a vital role in ensuring stable, reliable and normal work under the states of starting, climbing, emergency maneuvering and the like; the whole set of test system is comprehensive, good in reliability, good in economic performance and simple in structure.
Disclosure of Invention
The utility model provides a microminiature aviation turbine engine oil spout ring flow test system, this test system can discover effectively that the inhomogeneous problem of oil spout that microminiature aviation turbine engine oil spout ring appears, especially to establishing the basis for the inside flow field of oil spout ring of study and making the analysis in the future, provide the reference suggestion for the design of microminiature aviation turbine engine in future; the mass flow of fuel at the outlet of each fuel injection needle of the fuel injection ring of each microminiature aviation turbine engine can be measured through the flow testing system, so that whether the fuel flow at the outlet of each fuel injection needle is uniform or not is verified; the pressure regulator adopts a stepless speed-regulating pressure regulator, so that the fuel flow at the outlet of each fuel injection needle can be more accurately measured under the condition of different inlet total pressures; the flow testing system can ensure that various microminiature aviation turbine engines play a vital role in ensuring stable, reliable and normal work under the states of starting, climbing, emergency maneuvering and the like; the whole set of test system is comprehensive, good in reliability, good in economic performance and simple in structure.
The invention adopts a technical scheme that:
a microminiature aviation turbine engine oil spout ring flow test system, by oil spout ring part, fuel tank part, pressure measurement adjusting part and four major components such as the collection device make up, the said oil spout ring part includes oil spout ring oil inlet pipe, ring body and oil spray needle; the fuel tank component comprises an engine fuel tank, an engine fuel oil filter and an engine fuel pump; the pressure measuring part comprises a pressure regulator, a pressure regulating capillary (S1), a pressure display, a pressure capillary (S2), a fuel two-way joint (C1), a fuel three-way joint (C1) and a fuel three-way joint (C2);
further, the engine fuel oil filter is arranged in the engine fuel tank, the engine fuel tank is a hard fuel tank, the engine fuel oil filter is connected with the two-way fuel connector (C1) through a fuel pipe (L1), and the engine fuel pump is connected with the two-way fuel connector (C1) through a fuel pipe (L2);
further, the engine fuel pump is connected with a power supply through a lead (L1); the engine fuel pump is connected with the fuel three-way joint (C1) through a fuel pipe (L3);
further, the pressure regulating meter is connected with the fuel three-way joint (C1) through the pressure regulating capillary tube (S1); the fuel three-way joint (C1) is connected with the fuel three-way joint (C2) through a fuel pipe (L4);
further, the pressure display is connected with the fuel three-way joint (C2) through the pressure capillary (S2);
further, the oil inlet pipe of the oil injection ring is connected with the fuel three-way joint (C2) through a fuel pipe (L5); the oil injection needle is connected with the collecting device through a fuel oil pipe (L6), and the number of the oil injection needle is the same as that of the collecting device;
the beneficial effects of the invention are:
1. the utility model can measure the fuel mass flow at the outlet of each fuel injection needle of the fuel injection ring of each microminiature aircraft turbine engine through the flow measuring system, thereby verifying whether the fuel flow at the outlet of each fuel injection needle is even;
2. the utility model adopts the stepless speed regulation and pressure regulation meter, which can more accurately regulate the fuel flow at the outlet of each fuel injection needle under the condition of total pressure at different inlets;
3. the whole set of flow test system of the utility model can ensure that various microminiature aviation turbine engines play a crucial role in ensuring stable, reliable and normal work under the states of starting, climbing, emergency maneuvering and the like;
4. the utility model discloses a whole set of flow test system is comprehensive, good reliability, economic performance good, simple structure.
Drawings
FIG. 1 is a schematic view of the principle of the system for testing the fuel injection circulation flow of the microminiature aircraft turbine engine of the present invention
FIG. 2 is a schematic view of the fuel injection circulation flow test system of the micro-miniature aero-turbine engine of the present invention
FIG. 3 is a schematic view of the fuel injection ring component of the present invention
The parts in the drawings are numbered as follows:
1: injector ring component, 11: oil injection ring oil inlet pipe, 12: ring body, 13: an injection needle; 2: fuel tank component, 21: engine fuel tank, 22: oil filter for engine fuel oil, 23: engine fuel pump, 24: power supply, 25: fuel two-way joint (C1), 26: fuel three-way joint (C1), 27: fuel pipes (L1), 28: fuel pipes (L2), 29: fuel pipes (L3), 210: a lead (L1); 3: pressure measurement means, 31: pressure regulating meter, 32: pressure-regulating capillary (S1), 33: pressure display, 34: pressure capillary (S2), 35: fuel three-way joints (C2), 36: fuel pipes (L4), 37: fuel pipes (L5), 38: a fuel pipe (L6); 4: a collection device;
Detailed Description
The following detailed description of the preferred embodiments of the present invention is provided to enable those skilled in the art to more easily understand the advantages and features of the present invention, and to make clear and definite definitions of the protection scope of the present invention.
As shown in fig. 1 to 3, the system for testing the flow of the fuel injection ring of the micro-aircraft turbine engine in the embodiment comprises four major components, namely a fuel injection ring component 1, a fuel tank component 2, a pressure measurement adjusting component 3, a collecting device 4 and the like, and is characterized in that: the oil injection ring component 1 comprises an oil injection ring oil inlet pipe 11, a ring body 12 and an oil injection needle 13; the fuel tank component 2 comprises an engine fuel tank 21, an engine fuel filter (22) and an engine fuel pump 23; the pressure measurement adjusting part 3 comprises a pressure regulator 31, a pressure adjusting capillary (S1)32, a pressure display 33, a pressure capillary (S2)34, a fuel two-way joint (C1), a fuel three-way joint (C1)26 and a fuel three-way joint (C2) 35;
in this embodiment, the engine fuel oil filter 22 is arranged in the engine fuel tank 21, the oil delivery port of the engine fuel oil filter 22 is provided with a metal oil filter to prevent impurities in fuel oil from entering the fuel oil pipe (L1)27, the engine fuel tank 21 is a hard fuel tank and can meet the requirement of pressurizing the engine fuel tank 21, and the engine fuel tank 21 provides required fuel oil for the whole flow test system; the engine fuel filter 22 is connected with the fuel two-way joint (C1)25 through a fuel pipe (L1)27, and the engine fuel pump 23 is connected with the fuel two-way joint (C1)25 through a fuel pipe (L2) 28; the engine fuel pump 23 is connected to the power supply 24 by a lead (L1)210, and the power supply 24 provides power to the engine fuel pump 23 to draw fuel out of the engine fuel tank 21; the engine fuel pump 23 is connected to the fuel three-way joint (C1)26 through a fuel pipe (L3) 29; the pressure regulator 31 is connected with the fuel oil three-way joint (C1)26 through the pressure regulating capillary (S1), the pressure regulator 31 is stepless speed regulating, and the total inlet pressure of the fuel injection ring fuel inlet pipe 11 under different pressure conditions can be set, so that multiple groups of experiments under different pressure conditions are met; the fuel three-way joint (C1)26 is connected with the fuel three-way joint (C2)35 through a fuel pipe (L4) 36; the pressure display 33 is connected with the fuel three-way joint (C2)35 through the pressure capillary (S2)34, and the pressure display 33 can display the pressure value set by the pressure regulator 31; the oil inlet pipe 11 of the oil injection ring is connected with the fuel three-way joint (C2)35 through a fuel pipe (L5) 37; the fuel injection needle 13 is connected with the collecting device 4 through a fuel pipe (L6)38, and the number of the fuel injection needles 13 is the same as that of the collecting device 4, so that the fuel mass flow at the outlet of each fuel injection needle 13 can be accurately read;
it is obvious to a person skilled in the art that the invention is not restricted to details of the above-described exemplary embodiments, but that it can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
The above only is the embodiment of the present invention, not limiting the patent scope of the present invention, all of which utilize the equivalent structure or equivalent flow transformation made by the contents of the specification and the drawings or indirectly applied to other related technical fields, all included in the same principle in the protection scope of the present invention.
Claims (6)
1. The utility model provides a microminiature aviation turbine engine oil spout ring flow test system, comprises four major components such as oil spout ring part (1), fuel tank part (2), pressure measurement adjusting part (3) and collection device (4), its characterized in that: the oil injection ring component (1) comprises an oil injection ring oil inlet pipe (11), a ring body (12) and an oil injection needle (13); the fuel tank component (2) comprises an engine fuel tank (21), an engine fuel filter (22) and an engine fuel pump (23); the pressure measurement adjusting part (3) comprises a pressure regulator (31), pressure adjusting capillary tubes (S1) (32), a pressure display (33), pressure capillary tubes (S2) (34), fuel two-way joints (C1) (25), fuel three-way joints (C1) (26) and fuel three-way joints (C2) (35).
2. The system for testing fuel injection ring flow of the microminiature aircraft turbine engine as claimed in claim 1, wherein: the engine fuel oil filter (22) is arranged in the engine fuel tank (21), the engine fuel tank (21) is a hard fuel tank, the engine fuel oil filter (22) is connected with the fuel two-way joint (C1) (25) through a fuel pipe (L1) (27), and the engine fuel pump (23) is connected with the fuel two-way joint (C1) (25) through a fuel pipe (L2) (28).
3. The system for testing fuel injection ring flow of the microminiature aircraft turbine engine as claimed in claim 1, wherein: the engine fuel pump (23) is connected with the power supply (24) through a lead (L1) (210); the engine fuel pump (23) is connected with the fuel three-way joints (C1) (26) through fuel pipes (L3) (29).
4. The system for testing fuel injection ring flow of the microminiature aircraft turbine engine as claimed in claim 1, wherein: the pressure regulating meter (31) is connected with the fuel three-way joints (C1) (26) through the pressure regulating capillary tubes (S1) (32); the fuel three-way joints (C1) (26) are connected with the fuel three-way joints (C2) (35) through fuel pipes (L4) (36).
5. The system for testing fuel injection ring flow of the microminiature aircraft turbine engine as claimed in claim 1, wherein: the pressure display (33) is connected with the fuel three-way joint (C2) (35) through the pressure capillary (S2) (34).
6. The system for testing fuel injection ring flow of the microminiature aircraft turbine engine as claimed in claim 1, wherein: the oil inlet pipe (11) of the oil injection ring is connected with the fuel three-way joints (C2) (35) through fuel pipes (L5) (37); the fuel injection needles (13) are connected with the collecting device (4) through fuel pipes (L6) (38), and the number of the fuel injection needles (13) is the same as that of the collecting device (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920997529.3U CN210426968U (en) | 2019-06-28 | 2019-06-28 | Microminiature aviation turbine engine oil spout ring flow test system |
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| CN201920997529.3U CN210426968U (en) | 2019-06-28 | 2019-06-28 | Microminiature aviation turbine engine oil spout ring flow test system |
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| CN210426968U true CN210426968U (en) | 2020-04-28 |
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| CN201920997529.3U Active CN210426968U (en) | 2019-06-28 | 2019-06-28 | Microminiature aviation turbine engine oil spout ring flow test system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112964474A (en) * | 2021-02-09 | 2021-06-15 | 中国航发哈尔滨东安发动机有限公司 | Aviation low-pressure fuel flow measuring system and method |
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2019
- 2019-06-28 CN CN201920997529.3U patent/CN210426968U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112964474A (en) * | 2021-02-09 | 2021-06-15 | 中国航发哈尔滨东安发动机有限公司 | Aviation low-pressure fuel flow measuring system and method |
| CN112964474B (en) * | 2021-02-09 | 2023-10-13 | 中国航发哈尔滨东安发动机有限公司 | Low-pressure fuel flow measurement system and method for aviation |
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