CN114876637A - Unsteady load engine inlet total pressure distortion simulation device, method and system - Google Patents
Unsteady load engine inlet total pressure distortion simulation device, method and system Download PDFInfo
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- 238000004088 simulation Methods 0.000 title claims abstract description 63
- 238000000034 method Methods 0.000 title claims abstract description 21
- 239000012530 fluid Substances 0.000 claims abstract description 59
- 230000010355 oscillation Effects 0.000 claims abstract description 48
- 238000002474 experimental method Methods 0.000 claims abstract description 36
- 238000009423 ventilation Methods 0.000 claims abstract description 17
- 238000012360 testing method Methods 0.000 claims description 9
- 230000001052 transient effect Effects 0.000 claims description 6
- 238000009434 installation Methods 0.000 claims description 4
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- 238000013016 damping Methods 0.000 description 2
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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Abstract
The invention discloses a device, a method and a system for simulating total pressure distortion of an engine inlet with unsteady load, wherein the device comprises an experimental rectifier, a rectifier inlet and a rectifier outlet, the rectifier outlet is communicated with an aeroengine to be tested, a simulation assembly comprises fins and an air-bleed pipeline, the fins are arranged in the experimental rectifier in a centrosymmetric manner, and the air-bleed pipeline is communicated with an air source arranged outside the experimental rectifier; the fluid oscillation assembly is arranged in the rib and comprises a ventilation cavity, an expansion port and a rotating piece, and the ventilation cavity is respectively communicated with the air-entraining pipeline and the expansion port; the rotating piece is arranged in the expansion port and is rotationally connected with the expansion port. The method can truly simulate the total pressure distortion of the inlet of the engine, and takes the simulation range and the experiment cost into consideration.
Description
Technical Field
The invention relates to the technical field of aero-engine experiments, in particular to an engine inlet total pressure distortion simulation device, method and system for unsteady loads.
Background
The aircraft engine is a highly complex and precise thermal machine, and is used as the heart of an aircraft, not only as the power for flying the aircraft, but also as an important driving force for promoting the development of aviation industry. The design and development of the aeroengine lasts for decades, and nearly half of the time is to carry out performance and reliability test experiments; the test experiment period is long, the cost is high, and the research and development process of the aero-engine is severely restricted;
generally, the test experiment for the aircraft engine generally follows the experiment process from a part, a component to a whole machine, from a ground bench experiment to an air flight experiment, from a typical design point experiment to a complex working condition experiment. The experiment carried out on the ground experiment bench is a key component of the whole engine experiment and is also the basis of the subsequent flight experiment, the significance is great, the data is critical, and the experiment is also the experiment with the longest period in all the aviation engine experiments.
At present, for an aircraft engine ground bench test, a typical work cycle and a test of a designed work point are generally carried out, then a total pressure distortion simulator is installed in a fairing to simulate different distortions, and further verify the stable work capacity of an engine; the common form of the common total pressure distortion simulator is a damping net or a damping grid, and the common total pressure distortion simulator is used for simply simulating the uneven total pressure of an inlet of an engine, has limited experimental capacity, is used for carrying out engine experiments as truly as possible, is more difficult to simulate the most dangerous working conditions of the real engine during air flight, seriously restricts the experimental progress and increases the experimental cost.
Therefore, a simulation device capable of truly simulating the total pressure distortion at the inlet of the engine and considering both the simulation range and the experiment cost is needed at present.
Disclosure of Invention
Therefore, the device, the method and the system for simulating the total pressure distortion of the inlet of the unsteady-load engine overcome the defects of the prior art.
In order to solve the above technical problem, the present invention provides an unsteady load engine inlet total pressure distortion simulation apparatus, including:
the test fairing is provided with a fairing inlet and a fairing outlet, the fairing outlet is communicated with the aeroengine to be tested, and the aeroengine to be tested sucks simulation airflow into the test fairing;
the simulation assembly comprises fins and an air guide pipeline, wherein the fins are arranged in the experiment rectifying piece in a centrosymmetric manner, and the symmetric centers of the fins are parallel to the installation axis of the aero-engine to be tested along the axial line of the experiment rectifying piece in the length direction; the air guide pipeline is communicated with an air source arranged outside the experiment rectifying piece;
the fluid oscillation assembly is arranged in the rib and comprises a ventilation cavity, an expansion port and a rotating piece, and the ventilation cavity is respectively communicated with the gas drainage pipeline and the expansion port; the rotating piece is arranged in the expansion port and is rotationally connected with the expansion port;
and the interference airflow of the air source enters the ventilation chamber through the air guide pipeline, is ejected out of the expansion port through the ventilation chamber, and is converted into distorted airflow through the interference airflow.
Furthermore, the symmetry center of a plurality of fins is parallel to the installation axis of the aero-engine to be tested along the axis of the length direction of the experimental fairing, and the distance between the symmetry center of a plurality of fins and the central axis of the experimental fairing along the length direction is as follows: 15% -25% of the outlet diameter of the fairing.
Furthermore, the distance between the expansion opening and the outlet of the rectifying piece is L, the diameter of the experimental rectifying piece is D, and L is more than or equal to 2D and less than or equal to 5D.
Furthermore, the length dimension of the fins is r, wherein r is more than or equal to 0.15D and less than or equal to 0.25D.
Further, the length of the fluid oscillating assembly is equal to the length of the rib.
Further, the ratio of the pressure at the connection of the bleed air line and the vent chamber to the ambient pressure is PR, where PR is: 1.2-1.5.
Further, the vent chamber includes a first chamber in communication with the inducing line, a vent channel, and a second chamber in communication with the first chamber through the vent channel.
The invention also provides an unsteady load engine inlet total pressure distortion simulation method, which is used for carrying out total pressure distortion simulation on the aero-engine to be tested, and comprises the following steps:
step S1: sucking a simulation airflow into the experiment fairing through an aeroengine to be tested;
step S2: and the interference airflow of an external air source is continuously sprayed out of the experiment rectifying piece through the simulation assembly, and the interference airflow moves to a preset position, so that the simulation airflow is converted into distorted airflow.
Further, the transient impulse swirl distortion simulation method of the aero-engine to be tested comprises the following steps:
and discontinuously opening a gas introducing pipeline communicated with the fluid oscillation assembly, so that the first interference air flow passing through the fluid oscillation assembly at the first preset position moves to the second preset position, the first interference air flow converts the analog air flow into first distorted air flow, and meanwhile, the second interference air flow passing through the fluid oscillation assembly at the second preset position moves to the first preset position, and the second interference air flow converts the analog air flow into second distorted air flow.
The invention also provides an unsteady load engine inlet total pressure distortion simulation system, which comprises the unsteady load engine inlet total pressure distortion simulation device and further comprises:
the aero-engine to be tested is installed at a fairing outlet of the engine inlet total pressure distortion simulation device and is communicated with the fairing outlet.
Compared with the prior art, the technical scheme of the invention has the following advantages:
the device, the method and the system for simulating the total pressure distortion of the engine inlet with the unsteady load fully utilize the characteristic of rapid switching of the airflow direction of the fluid oscillation assembly to rapidly control the airflow distortion of the section of the engine inlet, and have rapid response; through the combined control of the fluid oscillation assembly, the generation of various distortions is realized by using one set of equipment, the distortion intensity is adjustable, the experiment can be continuously carried out, and the experiment period of the aircraft engine is shortened; various unsteady loads generated by the whipping of the air flow are utilized, so that the distortion simulation of the cross section of the inlet of the engine is carried out, the traditional experiment that only the total pressure distortion simulation is carried out is replaced, the authenticity of the ground bench experiment is further improved, and the cost of the subsequent engine experiment is reduced.
Drawings
In order that the present disclosure may be more readily and clearly understood, reference will now be made in detail to the present disclosure, examples of which are illustrated in the accompanying drawings.
Fig. 1 is a schematic cross-sectional view of a total pressure distortion simulation apparatus of the present invention.
Fig. 2 is a schematic cross-sectional view of a fluidic oscillation assembly of the present invention.
Fig. 3 is a numerical simulation cloud chart of t-0 of the present invention.
Fig. 4 is a numerical simulation cloud plot of T-1/6T for the present invention.
Fig. 5 is a numerical simulation cloud plot of T-1/3T for the present invention.
Fig. 6 is a numerical simulation cloud plot of T-1/2T for the present invention.
Fig. 7 is a numerical simulation cloud plot of T-2/3T for the present invention.
Fig. 8 is a numerical simulation cloud plot of T-5/6T for the present invention.
Description reference numbers indicate: 1. experimental fairing, 2, simulation assembly, 10, fairing inlet, 11, fairing outlet, 20, fins, 21, symmetry center of the plurality of fins, 22, bleed air duct, 31, first chamber, 32, second chamber, 33, expansion port, 34, rotation member, 35, vent channel.
Detailed Description
The present invention is further described below in conjunction with the following figures and specific examples so that those skilled in the art may better understand the present invention and practice it, but the examples are not intended to limit the present invention.
In the description of the present invention, it is to be understood that the terms "center", "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "second" or "first" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; the connection can be mechanical connection, electrical connection or communication; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
Unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may be directly contacting the first and second features, or indirectly contacting the first and second features through intervening media. Furthermore, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements does not include a limitation to the listed steps or elements but may alternatively include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
Example one
Referring to fig. 1-8, the present invention provides an embodiment of an unsteady load engine inlet total pressure distortion modeling apparatus, comprising:
the experimental fairing 1 is provided with a fairing inlet 10 and a fairing outlet 11, the fairing outlet 11 is communicated with the aero-engine to be tested, and the size of the fairing outlet 11 is consistent with that of the inlet of the aero-engine to be tested;
the simulation assembly 2 comprises fins 20 and an air bleed pipeline 22, wherein the fins 20 are arranged in the experiment rectifying piece 1 in a centrosymmetric manner, and the symmetric centers of the fins 20 are parallel to the installation axis of the aero-engine to be tested along the axial line of the experiment rectifying piece in the length direction; the bleed air line 22 is in communication with a source of air arranged outside the experimental fairing 1;
a fluid oscillating assembly, which is arranged inside the rib 20 and comprises a ventilation chamber, an expansion port 33 and a rotating member 34, wherein the ventilation chamber is respectively communicated with the bleed air pipeline 22 and the expansion port 33; the rotating part 34 is disposed in the expanding opening 33, and is rotatably connected to the expanding opening 33.
Wherein, the simulation component 2 and the fluid oscillation component are arranged in the experimental rectification piece 1; the inlet 10 of the rectifying part is communicated with ambient air, the aero-engine to be tested is placed at the outlet 11 of the rectifying part and is communicated with the aero-engine to be tested, after the aero-engine to be tested is started, a simulated airflow is sucked, enters from the inlet 10 of the rectifying part and leaves from the outlet 11 of the rectifying part from the experimental rectifying part 1; the number of the fins 20 is at least three, and preferably four in the present embodiment; setting the total pressure distortion position of the inlet section of the aero-engine to be tested through the symmetry centers of the plurality of fins 20, wherein the symmetry centers of the plurality of fins 20 are set by experimenters according to experimental requirements; the total pressure distortion of the inlet section of the downstream engine is set by the positions of the plurality of fins 20, and is set by an experimenter according to experimental requirements.
Wherein, each fin 20 is provided with a fluid oscillation component and a gas drainage pipeline 22; and the length dimension of the rib 20 is the same as that of the fluid oscillating assembly; the ventilation cavity adopts a concave cavity; the rotor 34 is, but not limited to, a rotatable wedge, and the direction of the airflow of the fluidic oscillation assembly is controlled by the angular rotation of the rotor 34.
By adopting the technical scheme, the aircraft engine to be tested sucks simulated airflow into the experimental fairing 1, interference airflow is guided into the ventilation cavity of the rib 20 through the air guide pipeline 22, the interference airflow is sprayed out from the expansion port 33 through the ventilation cavity, the rotating part 34 rotates to a preset angle, the interference airflow moves to a preset position, and the simulated airflow is interfered by the interference airflow to form distorted airflow; the preset angle and the preset position are set by an experimenter according to actual simulation requirements;
through the combined control of a plurality of fluidic oscillators, the simulation of different kinds of unsteady loads can be realized; in the present embodiment, the ribs 20 arranged in a cross shape are taken as an example:
when the air guide pipeline 22 communicated with the fluid oscillation assembly at the first preset position is continuously opened and the fluid oscillation assembly at the second preset position is closed, the first interference air flow of the fluid oscillation assembly at the first preset position moves towards the first movement direction, the first interference air flow interferes with the simulated air flow to form a first distorted air flow, and then the first direction detached vortex of the aero-engine during real work is simulated;
when the air guide pipeline 22 communicated with the fluid oscillation assembly at the second preset position is continuously opened and the fluid oscillation assembly at the first preset position is closed, the air flows to the second movement direction through second interference air flows of the fluid oscillation assembly at the second preset position, and the second interference air flows interfere with the simulated air flows to form second distorted air flows so as to simulate second direction detached vortexes of the aero-engine during real work;
when all the air guide pipelines 22 communicated with the fluid oscillation component are opened discontinuously, the first interference airflow moves to the second preset position through the fluid oscillation component at the first preset position to interfere the simulated airflow to form first distorted airflow, the second interference airflow moves to the first preset position through the fluid oscillation component at the second preset position to interfere the simulated airflow to form second distorted airflow, and the transient rush swirling flow distortion of the aero-engine to be tested during real work is simulated through the first distorted airflow and the second distorted airflow.
Wherein, the first preset position is set by an experimenter, and the transverse position is referred to in the embodiment; the second preset position is set by an experimenter and refers to the longitudinal position in the embodiment; the first interference airflow refers to interference airflow passing through the fluid oscillation assembly at the first preset position; the second interference airflow refers to interference airflow passing through the fluid oscillation assembly at the second preset position; the first movement direction is set by an experimenter, and the longitudinal movement direction is referred to in the embodiment; the second movement direction is set by an experimenter, and the transverse movement direction is referred to in the embodiment; the first direction shedder vortex refers in this embodiment to a longitudinal shedder vortex, for example a shedder vortex caused by high angle of attack flight; the second direction shedder vortex is referred to in this embodiment as a transverse shedder vortex, for example a shedder vortex caused by high slip angle flight.
In this embodiment, when the bleed air duct 22 communicated with the fluid oscillating assembly is intermittently opened, taking the fluid oscillating assembly at the first longitudinal position and the fluid oscillating assembly at the second transverse position as an example, the interference air flow passing through the fluid oscillating assembly at the first longitudinal position is whipped from the first transverse direction to the second transverse direction, and when the rotating member 34 of the fluid oscillating assembly at the first longitudinal position is rotated from the second transverse direction to the first transverse direction, the bleed air duct 22 communicated with the fluid oscillating assembly at the first longitudinal position is closed, and thereafter when the rotating member 34 is rotated from the first transverse direction to the second transverse direction, the bleed air duct 22 communicated with the fluid oscillating assembly at the first longitudinal position is opened, that is, the fluid oscillating assembly at the first longitudinal position only generates the whipping from the first transverse direction to the second transverse direction; the fluidic oscillation assembly in the second longitudinal position is opposite to the fluidic oscillation assembly in the first longitudinal position; in the present embodiment, the first longitudinal direction and the second longitudinal direction refer to an up-down direction, and the first transverse direction and the second transverse direction refer to a left-right direction;
the interference airflow passing through the fluid oscillating assembly at the second transverse position is whipped from the first longitudinal direction to the second longitudinal direction, when the rotating member 34 of the fluid oscillating assembly at the second transverse position rotates from the second longitudinal direction to the first longitudinal direction, the bleed air pipeline 22 communicated with the fluid oscillating assembly at the second transverse position is closed, and when the rotating member 34 rotates from the first longitudinal direction to the second longitudinal direction, the bleed air pipeline 22 communicated with the fluid oscillating assembly at the second transverse position is opened, namely the fluid oscillating assembly at the second transverse position only produces the whipping of the interference airflow from the first longitudinal direction to the second longitudinal direction; the fluidic oscillation assembly in the first lateral position is opposite to the fluidic oscillation assembly in the first lateral position;
simulating the transient rush swirling flow distortion in the clockwise direction; and otherwise, simulating the transient rush swirling flow distortion in the counterclockwise direction.
The distance between the symmetry center of the plurality of fins 20 and the central axis of the experimental fairing 1 is: 15% -25% of the diameter of the outlet 11 of the fairing; the distance between the expansion port 33 and the fairing outlet 11 is L, the diameter of the experimental fairing 1 is D, wherein L is more than or equal to 2D and less than or equal to 5D, and L is adjusted by an experimenter according to experimental requirements; the length dimension of the fins 20 is r, wherein r is more than or equal to 0.15D and less than or equal to 0.25D; the ratio PR of the pressure at the connection of the bleed line 22 and the vent chamber to the ambient pressure is: 1.2-1.5; at the moment, the fluid oscillation assembly can generate a vector angle of 15-20 degrees; through the setting, the experimental effect of total pressure distortion simulation can be further improved.
Referring to fig. 2, the ventilation chamber includes a first chamber 31 and a second chamber 32, the first chamber 31 is communicated with the air bleed pipeline 22, and the second chamber 32 is communicated with the first chamber 31 through a ventilation channel 35; the airflow enters the first chamber 31 through the air-bleed duct 22, enters the second chamber 32 through the first chamber 31, enters the expanded opening 33 through the second chamber 32, and is ejected through the expanded opening 33, and the ejection direction of the airflow is regulated by the rotating member 34.
Referring to fig. 3-8, a single motion period T of 3.6 x 10 is selected -4 s, performing numerical simulation, as can be seen from fig. 3 to 8, during the oscillation of the fluid, the ejected air flow is influenced by the flow field in the second chamber 32, and at the outlet of the expanded port 33, and the fluid whipping is formed by the rotation of the rotating member 34, and the whipping of the fluid forms a force with a direction changing continuously in one period; where T in fig. 3-8 is a small period of T, which includes 6 small T.
Example two
Referring to fig. 1 to 8, the present invention provides an embodiment of an unsteady load engine inlet total pressure distortion simulation method, and an engine inlet total pressure distortion simulation device for unsteady load is used to perform total pressure distortion simulation on an aircraft engine to be tested, including the following steps:
a simulated airflow is sucked into the experiment rectifying piece through an aero-engine to be tested;
continuously opening a gas introducing pipeline 22 communicated with a fluid oscillation assembly at a first preset position, enabling a first interference airflow to move to a second preset position through the fluid oscillation assembly, and interfering a simulated airflow through the first interference airflow to form a first distorted airflow so as to simulate a first-direction body shedding vortex of an aeroengine to be tested during real work;
after the simulation of the first-direction body shedding vortex is completed, continuously opening an air introducing pipeline 22 communicated with a fluid oscillation assembly at a second preset position, enabling a second interference airflow to move to the first preset position through the fluid oscillation assembly, forming a second distorted airflow through the interference of the second interference airflow on the simulation airflow, and simulating the second-direction body shedding vortex generated by the aero-engine to be tested during real work.
When the fluid oscillation assembly at the first preset position is continuously started, the fluid oscillation assembly at the second preset position is closed, and the first interference air flow of the fluid oscillation assembly at the first preset position moves towards the second movement direction; when the fluid oscillation assembly at the second preset position is continuously opened, the fluid oscillation assembly at the first preset position is closed, and the second interference air flow passing through the fluid oscillation assembly at the second preset position moves towards the first movement direction.
Further, the rotational flow distortion simulation method of the aero-engine to be tested comprises the following steps:
and discontinuously opening an air guide pipeline 22 communicated with the fluid oscillation component, so that the first interference airflow moves to the second preset position through the fluid oscillation component at the first preset position, forming a first distorted airflow by interfering the simulated airflow through the first interference airflow, simultaneously moving the second interference airflow to the first preset position through the fluid oscillation component at the second preset position, forming a second distorted airflow by interfering the simulated airflow through the second interference airflow, and simulating the transient rush swirling flow distortion of the aero-engine to be tested during real work through the first distorted airflow and the second distorted airflow.
When all the fluid oscillation assemblies are intermittently started, the first interference airflow and the second interference airflow passing through the fluid oscillation assemblies continuously generate a shaking phenomenon.
EXAMPLE III
Referring to fig. 1 to 8, the present invention provides an embodiment of an unsteady load engine inlet total pressure distortion simulation system, including the above-mentioned unsteady load engine inlet total pressure distortion simulation apparatus, further including:
the aero-engine to be tested is installed at a fairing outlet of the engine inlet total pressure distortion simulation device and communicated with the fairing outlet.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Various other modifications and alterations will occur to those skilled in the art upon reading the foregoing description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications of the invention may be made without departing from the spirit or scope of the invention.
Claims (10)
1. The engine inlet total pressure distortion analogue means of unsteady load, its characterized in that includes:
the test fairing is provided with a fairing inlet and a fairing outlet, the fairing outlet is communicated with the aeroengine to be tested, and the aeroengine to be tested sucks simulation airflow into the test fairing;
the simulation assembly comprises fins and an air bleed pipeline, wherein the fins are arranged in the experiment rectifying piece in a centrosymmetric manner, and the air bleed pipeline is communicated with an air source arranged outside the experiment rectifying piece;
the fluid oscillation assembly is arranged in the rib and comprises a ventilation cavity, an expansion port and a rotating piece, and the ventilation cavity is respectively communicated with the gas drainage pipeline and the expansion port; the rotating piece is arranged in the expansion port and is rotationally connected with the expansion port;
and the interference airflow of the air source enters the ventilation chamber through the air guide pipeline, is ejected out of the expansion port through the ventilation chamber, and is converted into distorted airflow through the interference airflow.
2. The unsteady load engine inlet total pressure distortion simulation device as claimed in claim 1, wherein the symmetry centers of a plurality of fins are parallel to the installation axis of the aero-engine to be tested along the axis of the experimental fairing in the length direction, and the distance between the symmetry centers of the plurality of fins and the central axis of the experimental fairing in the length direction is: 15% -25% of the outlet diameter of the fairing.
3. An unsteady load engine inlet total pressure distortion simulation device according to claim 1, wherein the distance between the expansion port and the outlet of the fairing is L, the diameter of the experimental fairing is D, and L is greater than or equal to 2D and less than or equal to 5D.
4. A unsteady load engine inlet total pressure distortion simulation device as claimed in claim 3, characterized in that the length dimension of the ribs is r, wherein 0.15D ≦ r ≦ 0.25D.
5. An unsteady load engine inlet total pressure distortion simulation device as claimed in claim 4, characterized in that the length of the fluidic oscillation assembly is equal to the length dimension of the ribs.
6. A unsteady load engine inlet total pressure distortion simulation device as claimed in claim 1, wherein the ratio of the pressure at the connection of the bleed air line and the bleed chamber to the ambient pressure is PR, where PR is: 1.2-1.5.
7. An unsteady load engine inlet total pressure distortion simulation device according to claim 1, characterized in that the breather chamber comprises a first chamber communicating with the induction line, a breather passage, and a second chamber communicating with the first chamber through the breather passage.
8. An unsteady-load engine inlet total pressure distortion simulation method for performing total pressure distortion simulation on an aircraft engine to be tested by using the unsteady-load engine inlet total pressure distortion simulation device as defined in any one of claims 1 to 7, wherein the method comprises the following steps of:
step S1: sucking a simulation airflow into the experiment fairing through an aeroengine to be tested;
step S2: and the interference airflow of an external air source is continuously sprayed out of the experiment rectifying piece through the simulation assembly, and the interference airflow moves to a preset position, so that the simulation airflow is converted into distorted airflow.
9. The unsteady load engine inlet total pressure distortion simulation method of claim 8, wherein the transient rush swirling flow distortion simulation method of the aero-engine to be tested is as follows:
and discontinuously opening a gas introducing pipeline communicated with the fluid oscillation assembly, so that the first interference air flow passing through the fluid oscillation assembly at the first preset position moves to the second preset position, the first interference air flow converts the analog air flow into first distorted air flow, and meanwhile, the second interference air flow passing through the fluid oscillation assembly at the second preset position moves to the first preset position, and the second interference air flow converts the analog air flow into second distorted air flow.
10. An unsteady load engine inlet total pressure distortion simulation system comprising the unsteady load engine inlet total pressure distortion simulation apparatus as claimed in any one of claims 1 to 7, further comprising:
the aero-engine to be tested is installed at a fairing outlet of the engine inlet total pressure distortion simulation device and is communicated with the fairing outlet.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210384564.4A CN114876637A (en) | 2022-04-13 | 2022-04-13 | Unsteady load engine inlet total pressure distortion simulation device, method and system |
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| CN202210384564.4A CN114876637A (en) | 2022-04-13 | 2022-04-13 | Unsteady load engine inlet total pressure distortion simulation device, method and system |
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| CN202210384564.4A Pending CN114876637A (en) | 2022-04-13 | 2022-04-13 | Unsteady load engine inlet total pressure distortion simulation device, method and system |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5448881A (en) * | 1993-06-09 | 1995-09-12 | United Technologies Corporation | Gas turbine engine control based on inlet pressure distortion |
| CN104912668A (en) * | 2015-04-24 | 2015-09-16 | 南京航空航天大学 | Variable camber vane type spiral flow distortion generator |
| CN106153346A (en) * | 2016-07-20 | 2016-11-23 | 南京航天航空大学 | A kind of inflatable vane type swirl flow distortion generator and method for generation |
| CN107505138A (en) * | 2017-09-11 | 2017-12-22 | 南京航空航天大学 | A kind of complicated distortion generator for Compressor Stability experiment |
| CN112240831A (en) * | 2020-10-15 | 2021-01-19 | 厦门大学 | Design method of aero-engine intake temperature distortion generator |
| US20210278192A1 (en) * | 2020-03-06 | 2021-09-09 | Bell Textron Inc. | Concentric probe |
| CN113567141A (en) * | 2020-04-28 | 2021-10-29 | 中国航发商用航空发动机有限责任公司 | Distortion generating device and simulation method thereof and pressure distortion characteristic test system |
| CN113567142A (en) * | 2020-04-28 | 2021-10-29 | 中国航发商用航空发动机有限责任公司 | Air inlet simulation device, aircraft engine test device and air inlet simulation method |
-
2022
- 2022-04-13 CN CN202210384564.4A patent/CN114876637A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5448881A (en) * | 1993-06-09 | 1995-09-12 | United Technologies Corporation | Gas turbine engine control based on inlet pressure distortion |
| CN104912668A (en) * | 2015-04-24 | 2015-09-16 | 南京航空航天大学 | Variable camber vane type spiral flow distortion generator |
| CN106153346A (en) * | 2016-07-20 | 2016-11-23 | 南京航天航空大学 | A kind of inflatable vane type swirl flow distortion generator and method for generation |
| CN107505138A (en) * | 2017-09-11 | 2017-12-22 | 南京航空航天大学 | A kind of complicated distortion generator for Compressor Stability experiment |
| US20210278192A1 (en) * | 2020-03-06 | 2021-09-09 | Bell Textron Inc. | Concentric probe |
| CN113567141A (en) * | 2020-04-28 | 2021-10-29 | 中国航发商用航空发动机有限责任公司 | Distortion generating device and simulation method thereof and pressure distortion characteristic test system |
| CN113567142A (en) * | 2020-04-28 | 2021-10-29 | 中国航发商用航空发动机有限责任公司 | Air inlet simulation device, aircraft engine test device and air inlet simulation method |
| CN112240831A (en) * | 2020-10-15 | 2021-01-19 | 厦门大学 | Design method of aero-engine intake temperature distortion generator |
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