CN113418713B - Combined distortion generator of engine - Google Patents
Combined distortion generator of engine Download PDFInfo
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- CN113418713B CN113418713B CN202110686097.6A CN202110686097A CN113418713B CN 113418713 B CN113418713 B CN 113418713B CN 202110686097 A CN202110686097 A CN 202110686097A CN 113418713 B CN113418713 B CN 113418713B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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Abstract
The application belongs to the technical field of engine tests, and particularly relates to an engine combined distortion generator. The device includes engine intake duct distortion runner, runner picture peg (1), swirl generator (3) and gas generator (10), wherein, runner picture peg (1) certainly engine intake duct distortion runner inner wall stretches into to insert by picture peg actuating mechanism (2) drive size in the engine intake duct distortion runner, swirl generator (3) set up on a cross-section in the engine intake duct distortion runner to but produce the whirl through the deflection stator on it, swirl generator (3) set up through the tube coupling the outer gas generator (10) of engine intake duct distortion runner, through gas generator (10) to engine intake duct distortion runner produces high temperature gas. The distortion generating factor and the distortion intensity are adjustable and controllable, and the complex flow and dynamic process can be effectively simulated.
Description
Technical Field
The application belongs to the technical field of engine tests, and particularly relates to an engine combined distortion generator.
Background
With the development of aviation technology, the design layout of the aircraft is more and more compact, the performance is higher and higher, and the aerodynamics and the flow path are more and more complex. This makes the engine need work under all kinds of complicated operating modes, and adverse effect is caused to the job stabilization nature of engine to abominable operational environment can produce different kinds of distortions at the engine import. For example: a. the flight performance of a modern fighter gradually extends to the left boundary of the envelope curve, and the fast pointing capability, the large attack angle maneuver and even the over-stall maneuver of a side-weight nose can generate a large-range flow separation in an air inlet channel to further form pressure distortion; b. in consideration of stealth, an S-shaped air inlet channel is commonly adopted by a new generation of fighter, and the air inlet channel is turned for multiple times, so that a large-scale vortex can be formed in front of an engine inlet, and rotational flow distortion is generated; c. modern fighters are more and more compact in structure, small in distance between weapon systems such as aeroguns and missile hangers and air inlet channels, and easy to swallow high-temperature waste gas to form temperature distortion when using weapons. In addition, the carrier-based aircraft may also generate temperature distortion when the aircraft operates in front of the aircraft carrier drift plate, during the steam catapult takeoff process, and when the aircraft passes through a smoke area.
At present, the following three forms mainly exist for carrying out the distortion of an engine air inlet:
1) pressure distortion generated by distortion simulation plate or air inlet duct insertion plate
The required pressure distortion can be generated by simulating a distortion map before the inlet of the engine through the distortion simulation plate, but each distortion simulation plate can only simulate one type of distortion map, needs a large amount of processing and modification work and does not have the adjusting capability.
The air inlet duct plugboard is widely used as a pressure distortion generator, but only a fixed type of distortion map can be generated, and the capability of simulating combined distortion is not provided.
2) Generating rotational flow distortion by means of fixed guide vanes, vortex generators or rotational flow distortion simulation nets
The simple structure of stator and vortex generator also can produce the whirl distortion of enough intensity, but does not possess the ability of real-time regulation among the test process, can adjust only after the single test finishes, leads to test cycle length, and the test cost is high to only can simulate specific form whirl distortion.
The rotational flow distortion simulation net can simulate rotational flow distortion, but a large amount of flow field simulation and machining and shaping work are needed in the early stage, each simulation net can only generate one corresponding distortion map, repeated superposition of a base net and the distortion net is needed, the machining and assembling precision requirements of a test piece are high, the assembling and disassembling workload is large, the test piece is easy to damage, and the machining cost and the testing cost of the whole tester are high.
3) Temperature distortion by gasifier
The temperature distortion can be generated by placing a gas generator in front of the inlet of the engine, but only the simulation of the pure temperature distortion can be realized at present.
During the engine installation work, the above intake distortion does not exist independently, but appears in the form of multi-distortion combination. The current distortion simulation method only aims at a single distortion form, and the research of the multi-distortion combined simulation method is blank.
Disclosure of Invention
In order to solve the technical problem, the application provides an engine combination distortion generator, mainly include engine intake duct distortion runner, runner picture peg, whirl generator and gas generator, wherein, the runner picture peg certainly engine intake duct distortion runner inner wall stretches into to insert by picture peg actuating mechanism drive size in the engine intake duct distortion runner, whirl generator sets up on a cross-section in the engine intake duct distortion runner to but produce the whirl through the deflection stator thereon, whirl generator passes through the pipe connection and sets up the outer gas generator of engine intake duct distortion runner, through gas generator to engine intake duct distortion runner produces the high temperature gas.
Preferably, the swirl generator includes fixed blade and movable blade, and a plurality of fixed blade's one end is in central axis department in the engine intake duct distortion runner joins, and the other end radially extends to engine intake duct distortion runner inner wall along engine intake duct distortion runner, fixed blade has the inner channel, gas generator is connected to inner channel one end, and other parts are provided with a plurality of high temperature fumaroles, movable blade articulates on the fixed blade.
Preferably, the movable blade is driven to deflect by a bucket drive mechanism.
Preferably, the movable blade driving mechanism is a cylinder, an output end of the cylinder is hinged to a connecting rod, and the other end of the connecting rod is connected to the movable blade.
Preferably, it is a plurality of fixed blade passes through the gas injection ring to be fixed, the gas injection ring is fixed engine intake duct distortion runner inner wall, just the gas injection ring passes through gas pipe connection gas generator, and the gas injection ring is connected to respectively through a plurality of exports fixed blade's inner channel.
Preferably, the high temperature gas injection holes are uniformly distributed on the movable blade.
Preferably, the high-temperature gas injection hole is arranged on the side wall of the movable blade and used for guiding the high-temperature gas flowing out of the high-temperature gas injection hole to move along the direction perpendicular to the flow of the gas flow in the distorted flow passage of the engine air inlet.
Preferably, the flow passage inserting plate is positioned in front of the swirl generator along the flowing direction of the air flow in the engine air inlet distortion flow passage.
The application provides a pressure-temperature-rotational flow combined distortion simulation engine combined distortion generator capable of being adjusted in real time aiming at simulation requirements of combined distortion, through combination of an adjustable inserting plate and an adjustable guide vane and a high-temperature gas valve arranged in the adjustable guide vane, and mainly has the following advantages:
1) the distortion simulation equipment has a real-time adjusting function, and different distortion maps can be matched by adjusting the parameters of the tester in one test, so that the test period is effectively shortened, and the test cost is reduced;
2) the single distortion and the combined distortion can be simulated by one set of tester, the functions of a plurality of sets of testers can be realized by one set of tester, the repeated construction of the test bed due to the limitation of the functions of the testers is avoided, the infrastructure construction cost is reduced, and the application prospect is wide.
Drawings
Fig. 1 is a schematic diagram of a combined distortion generator according to a preferred embodiment of the present invention.
Fig. 2 is a schematic structural diagram of the vortex generator according to the embodiment shown in fig. 1 of the present application.
FIG. 3 is a schematic view of the stationary vane and gas injection ring structure of the embodiment of FIG. 1 of the present application.
FIG. 4 is a schematic view of the movable vane adjustment of the embodiment of FIG. 1 of the present application.
FIG. 5 is a schematic diagram of the embodiment of FIG. 1 of the present application showing pressure distortion alone.
FIG. 6 is a schematic diagram of the embodiment of FIG. 1 of the present application showing the independent generation of swirling pressure distortion.
FIG. 7 is a schematic diagram of the embodiment of FIG. 1 of the present application showing temperature distortion alone.
FIG. 8 is a schematic diagram of the embodiment of the present application shown in FIG. 1 showing the combined distortion of pressure, swirl and temperature.
The gas turbine comprises a flow channel plug board 1, a plug board driving mechanism 2, a vortex generator 3, a movable blade 4, a movable blade 5, a fixed blade 6, a high-temperature gas jet hole 7, a gas injection ring 8, a gas guide pipe 9, a gas generator 10, a low-pressure area 11, a vortex 12 and a high-temperature gas 13.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are implementations that are part of this application and not all implementations. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The application provides an engine combination distortion generator, as shown in fig. 1-8, mainly include engine intake duct distortion runner, runner picture peg 1, swirl generator 3 and gas generator 10, wherein, runner picture peg 1 certainly engine intake duct distortion runner inner wall stretches into to insert by picture peg actuating mechanism 2 drive size in the engine intake duct distortion runner, swirl generator 3 sets up on a cross-section in the engine intake duct distortion runner to but produce the whirl through the deflector vane thereon, swirl generator 3 sets up through the pipe connection the outer gas generator 10 in engine intake duct distortion runner, through gas generator 10 to engine intake duct distortion runner produces high temperature gas.
In some optional embodiments, the swirl generator 3 includes fixed blade 6 and movable blade 4, and the one end of a plurality of fixed blade 6 is in central axis department in the engine intake distortion runner joins, and the other end radially extends to engine intake distortion runner inner wall along engine intake distortion runner, fixed blade 6 has the inner channel, gas generator is connected to inner channel one end, and other parts are provided with a plurality of high temperature fumaroles 7, movable blade 4 articulates on fixed blade 6.
In some alternative embodiments, the movable blade 4 is driven to deflect by a bucket drive mechanism 5.
In some alternative embodiments, the bucket driving mechanism 5 is a ram, and the output end of the ram is hinged to a connecting rod, and the other end of the connecting rod is connected to the movable blade 4.
In some optional embodiments, a plurality of the fixed blades 6 are fixed by an injection ring 8, the injection ring 8 is fixed on the inner wall of the engine inlet distortion flow passage, the injection ring 8 is connected with a gas generator 10 through a gas conduit 9, and the injection ring 8 is respectively connected to the inner channels of the fixed blades 6 through a plurality of outlets.
In some alternative embodiments, the high temperature gas injection holes 7 are evenly distributed on the movable blade 4.
In some alternative embodiments, the high temperature gas injection hole 7 is disposed on the side wall of the movable blade 4, and is used for guiding the high temperature gas flowing out from the high temperature gas injection hole 7 to move along a direction perpendicular to the flow of the gas in the engine inlet distortion flow passage.
In some alternative embodiments, the flow passage insert plate 1 is located in front of the swirl generator 3 along the direction of air flow in the engine inlet distortion flow passage.
The scheme has four working modes:
the first working mode is as follows: pressure distortion alone (as shown in figure 5). All the movable blades 4 of the swirl generator 3 remain parallel to the incoming flow direction, and the gas generator 10 is in the closed state. At this time, the range of the low pressure region 11 within the flow passage is changed by adjusting the insertion depth of the flow passage insertion plate 1 in the flow passage by the insertion plate driving mechanism 2, thereby generating a desired pressure distortion.
And a second working mode: swirl pressure distortion alone (as shown in figure 6). The flow passage insert plate 1 is drawn out of the flow passage and the gasifier 10 is in a closed state. At this time, the rotational flow distortion is produced by changing the angle of deflection of each movable blade 4 in the rotational flow generator 3 by the rotor blade driving mechanism 5 to generate a specific rotational flow 12 in the flow passage.
And a third working mode: temperature distortion alone (as shown in figure 7). The flow passage insert plate 1 extracts the flow passage, and all movable blades 4 of the vortex generator 3 are kept parallel to the incoming flow direction. The gas generator 10 is operated, and the generated high temperature gas flows into a specific region of the fixed vane 6 through the gas guide pipe 9 via the gas injection ring 8, and the high temperature gas 13 is injected into the flow passage from the high temperature exhaust hole 7 of the region, thereby generating temperature distortion in the flow passage.
And a fourth working mode: creating a pressure-swirl-temperature combined distortion (as shown in figure 8). The insertion depth of the adjustable insertion plate 1 in the flow channel is adjusted through the insertion plate driving mechanism 2 to generate a low-pressure area 11, the deflection angle of each movable blade 4 on the swirl generator 3 is changed through the movable blade driving mechanism 5 to generate swirl 12, high-temperature gas generated by the gas generator 10 flows into a specific area of the fixed blade 6 through the gas guide pipe 9 and the gas injection ring 8, and high-temperature gas 13 is injected into the flow channel from a high-temperature exhaust hole 7 in the area, so that pressure-swirl-temperature combined distortion is generated in the flow channel.
The method and the device aim at the distortion simulation of multi-factor composition, the distortion generating factors and the distortion strength are adjustable and controllable, and the complex flow and dynamic process can be effectively simulated.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. The utility model provides an engine combination distortion generator, characterized in that, including engine intake duct distortion runner, runner picture peg (1), swirl generator (3) and gas generator (10), wherein, runner picture peg (1) certainly engine intake duct distortion runner inner wall stretches into to drive by picture peg actuating mechanism (2) and insert the size in the engine intake duct distortion runner, swirl generator (3) set up on a cross-section in the engine intake duct distortion runner, and produce the whirl through the deflectable stator thereon, swirl generator (3) set up through the tube coupling the gas generator (10) outside engine intake duct distortion runner, through gas generator (10) to engine intake duct distortion runner produces high temperature gas;
the swirl generator (3) comprises fixed blades (6) and movable blades (4), one ends of the fixed blades (6) are converged at the central axis in the engine intake channel distortion flow channel, the other ends of the fixed blades radially extend to the inner wall of the engine intake channel distortion flow channel along the engine intake channel distortion flow channel, the fixed blades (6) are provided with inner channels, one ends of the inner channels are connected with a fuel gas generator, other parts of the inner channels are provided with a plurality of high-temperature gas injection holes (7), and the movable blades (4) are hinged to the fixed blades (6);
the fixed blades (6) are fixed through an air injection ring (8), the air injection ring (8) is fixed on the inner wall of the engine inlet channel distortion flow channel, the air injection ring (8) is connected with a fuel gas generator (10) through a fuel gas conduit (9), and the air injection ring (8) is respectively connected to the inner channels of the fixed blades (6) through a plurality of outlets;
the high-temperature gas injection hole (7) is further arranged on the side wall of the movable blade (4) and used for guiding high-temperature gas flowing out of the high-temperature gas injection hole (7) to move along the direction perpendicular to the flowing direction of gas flow in an engine gas inlet distortion flow passage.
2. The engine combined distortion generator of claim 1, characterized in that the movable vane (4) is driven to deflect by a bucket drive mechanism (5).
3. The engine compound distortion generator of claim 2 wherein the bucket drive mechanism (5) is a ram with an output end hinged to a link with the other end connected to the movable vane (4).
4. The engine combined distortion generator of claim 1 characterized in that the high temperature gas injection holes (7) are evenly distributed on the movable blade (4).
5. The combined distortion generator of an engine as claimed in claim 1, wherein the flow passage insert plate (1) is located in front of the swirl generator (3) in the direction of flow of air in the inlet distortion flow passage of the engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110686097.6A CN113418713B (en) | 2021-06-21 | 2021-06-21 | Combined distortion generator of engine |
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| CN202110686097.6A CN113418713B (en) | 2021-06-21 | 2021-06-21 | Combined distortion generator of engine |
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| CN113418713A CN113418713A (en) | 2021-09-21 |
| CN113418713B true CN113418713B (en) | 2022-09-30 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114001964B (en) * | 2021-11-02 | 2024-02-02 | 中国航发沈阳发动机研究所 | Flight table with large-span S-bend air inlet and exhaust system |
| CN114013668B (en) * | 2021-11-10 | 2024-04-09 | 中国航发沈阳发动机研究所 | Aeroengine fan capable of actively adjusting electromagnetic scattering characteristics |
| CN114435625B (en) * | 2021-12-31 | 2023-09-05 | 中国航发沈阳发动机研究所 | High-temperature airflow simulation test method for engine air inlet channel suction |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104912668B (en) * | 2015-04-24 | 2017-04-19 | 南京航空航天大学 | Variable camber vane type spiral flow distortion generator |
| CN106153346B (en) * | 2016-07-20 | 2019-07-19 | 南京航空航天大学 | A kind of inflatable vane type swirl flow distortion generator and method for generation |
| CN107505138B (en) * | 2017-09-11 | 2019-05-14 | 南京航空航天大学 | A kind of complicated distortion generator for Compressor Stability test |
| US20200080477A1 (en) * | 2018-09-07 | 2020-03-12 | United Technologies Corporation | Prediction of inlet distortion of boundary layer ingesting propulsion system |
| CN110044628B (en) * | 2019-03-27 | 2020-04-24 | 南京航空航天大学 | Dynamic distortion generator and method for stability test of gas compressor |
| CN209878328U (en) * | 2019-05-22 | 2019-12-31 | 厦门大学 | Integrated propane combustion type temperature distortion generating device |
| CN112179666B (en) * | 2020-09-18 | 2022-12-20 | 中国航发四川燃气涡轮研究院 | Multipurpose distortion generator based on distributed movable plugboard |
| CN112240831B (en) * | 2020-10-15 | 2021-06-29 | 厦门大学 | Design method of aero-engine intake temperature distortion generator |
| CN112284751B (en) * | 2020-10-16 | 2023-01-13 | 中国航发四川燃气涡轮研究院 | Distortion test device with adjustable distortion characteristic |
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