CN115685568A - Method and device for capturing particle foreign matter in tail jet flow field of aircraft engine by using optical trap - Google Patents
Method and device for capturing particle foreign matter in tail jet flow field of aircraft engine by using optical trap Download PDFInfo
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- 230000001276 controlling effect Effects 0.000 claims abstract description 9
- 239000013618 particulate matter Substances 0.000 claims description 8
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Abstract
The invention discloses a method and a device for capturing particle foreign matter in a tail jet flow field of an aeroengine, wherein the device comprises a laser, an Axicon lens and a zoom lens group, the laser is used for generating parallel laser and providing energy required by the optical trap, the Axicon lens is used for generating a non-diffraction light beam by using the parallel laser so as to obtain the optical trap for capturing the particle foreign matter in the tail jet flow field of the aeroengine, and the zoom lens group is used for regulating and controlling the position of the non-diffraction light beam so that the optical trap pushes the particle foreign matter in the tail jet flow field of the aeroengine to a tail jet side. According to the invention, through regulation and control of the position of the diffraction-free light trap, the particulate matters in the tail jet of the aero-engine are gradually pushed to the tail jet side under the constraint action of the diffraction-free light trap, so that the collection of the particulate matters in the tail jet of the aero-engine is realized, and the technical problem of high difficulty in monitoring the state of the aero-engine aiming at particulate foreign matters in the tail jet flow field of the aero-engine at present is solved.
Description
Technical Field
The invention relates to the technical field of aero-engine state monitoring, in particular to a method and a device for capturing particle foreign matter in an aero-engine tail jet flow field by using an optical trap.
Background
The tail jet flow field of the aero-engine is a high-temperature and high-speed combustion flow field, wherein the type and the number of particles in the flow field reflect the health state of an aero-engine gas circuit.
However, due to high temperature and high speed, particles are difficult to capture to carry out excitation of atomic spectrum, and further, the difficulty in monitoring the state of the aircraft engine aiming at particle foreign matters in the jet flow field of the aircraft engine tail is high.
Disclosure of Invention
The invention mainly aims to provide a method and a device for capturing particle foreign matters in an aeroengine tail jet flow field by using an optical trap, aiming at realizing the collection of the particles in the aeroengine tail jet by regulating and controlling the position of a diffraction-free optical trap and gradually pushing the particles to the tail jet side under the constraint action of the diffraction-free optical trap when the particles in the aeroengine tail jet flow field are sprayed, and solving the technical problem of high difficulty in monitoring the state of the aeroengine aiming at the particle foreign matters in the aeroengine tail jet flow field at present.
In order to achieve the above object, the present invention provides an optical trap capturing device for particle foreign matters in an aircraft engine tail jet flow field, comprising:
the laser is used for generating parallel laser and providing energy required by the optical trap;
the Axicon lens is used for generating a non-diffraction light beam by utilizing the parallel laser so as to obtain an optical trap for capturing particle foreign matters in a tail jet flow field of the aeroengine;
and the zoom lens group is used for regulating and controlling the position of the non-diffracted light beam so as to enable the light trap to push the particle foreign matters in the tail jet flow field of the aeroengine to the tail jet side.
Optionally, the parameter expressions of the non-diffracted beam and the Axicon lens are as follows:
z max ＝R·[cotη 3 -tanθ]；
wherein z is max The maximum diffraction-free region on the optical axis from the cone vertex of the Axicon lens, R is the radius of the Axicon lens, eta 3 Theta is the angle between the emergent beam and the Axicon and is the cone angle of the Axicon lens.
Optionally, the zoom lens group includes a lens a and a lens B, the lens a is configured to convert the non-diffracted light beam generated by the Axicon lens into an annular light source in an object space of the lens B, and the lens B is configured to convert the annular light source into the non-diffracted light beam with new parameters.
Optionally, the expression of the regulation relationship between the lens a and the lens B for the non-diffracted light beam is as follows:
l 2 ＝f 2 (f 1 2 +f 1 f 2 -f 2 l 1 )/f 1 2 ；
wherein l 1 Distance from Axicon lens to lens A, l 2 Distance of lens B to the non-diffracted beam with new parameters, f 1 Distance of lens A from annular light source, f 2 Is the distance from lens B to the annular light source.
Alternatively, the relative positions of the lens a and the lens B are controlled to move.
Optionally, an included angle between the laser and the Axicon lens satisfies the following constraint condition:
wherein eta is an included angle of a parallel light beam emitted by the laser irradiating an Axicon lens incident plane, theta is a cone angle of the Axicon lens, n is a refractive index of the Axicon lens, lambda is a wavelength emitted by the laser, and z is a distance in a propagation direction of a non-diffraction light beam.
Optionally, the laser is fixed to the fixing table, and the emitting laser is adjusted in the attitude by a manual fine adjustment device with adjustable degree of freedom.
Optionally, the relative distance between the laser and the Axicon lens is fixed and adjusted by a clamp.
In addition, in order to achieve the above object, the present invention further provides an optical trap capturing method for particulate matter in an aircraft engine tail jet flow field, which is used for the above optical trap capturing device for particulate matter in an aircraft engine tail jet flow field, and the method includes the following steps:
parallel laser is generated through a laser, and energy required by an optical trap is provided;
generating a non-diffraction light beam by utilizing the parallel laser through an Axicon lens to obtain an optical trap for capturing particle foreign matters in a tail jet flow field of the aeroengine;
and regulating and controlling the position of the non-diffracted light beam through a zoom lens group so that the light trap pushes the particle foreign matters in the tail jet flow field of the aeroengine to the tail jet side.
The invention provides a method and a device for capturing particle foreign matter in an aircraft engine tail jet flow field, wherein the device comprises a laser, an Axicon lens and a zoom lens group, the laser is used for generating parallel laser and providing energy required by an optical trap, the Axicon lens is used for generating a non-diffraction light beam by using the parallel laser so as to obtain the optical trap for capturing the particle foreign matter in the aircraft engine tail jet flow field, and the zoom lens group is used for regulating and controlling the position of the non-diffraction light beam so as to enable the optical trap to push the particle foreign matter in the aircraft engine tail jet flow field to a tail jet side. According to the invention, through regulation and control of the position of the diffraction-free light trap, the particulate matters in the tail jet of the aero-engine are gradually pushed to the tail jet side under the constraint action of the diffraction-free light trap, so that the collection of the particulate matters in the tail jet of the aero-engine is realized, and the technical problem of high difficulty in monitoring the state of the aero-engine aiming at particulate foreign matters in the tail jet flow field of the aero-engine at present is solved.
Drawings
FIG. 1 is a schematic view of a particle foreign matter optical trap capturing device of an aircraft engine tail jet flow field;
FIG. 2 is a schematic non-diffractive optics of an Axicon lens of the present invention;
FIG. 3 is a schematic diagram of the incidence plane of an Axicon lens irradiated perpendicularly by a parallel laser beam according to the present invention;
FIG. 4 is a schematic view of a collimated laser beam impinging on the incident surface of an Axicon lens at an angle in accordance with the present invention;
FIG. 5 is a schematic of the non-diffraction zones of an Axicon lens of the invention;
FIG. 6 is a schematic representation of Poisson's diffraction spots corresponding to non-diffraction zones of the present invention;
FIG. 7 is a schematic diagram illustrating the principle of adjusting and controlling parameters of a non-diffractive beam by the zoom lens assembly of the present invention.
The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
It should be understood that the specific embodiments described herein are merely illustrative of the invention and do not limit the invention.
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all directional indicators (such as up, down, left, right, front, back \8230;) in the embodiments of the present invention are only used to explain the relative positional relationship between the components, the motion situation, etc. in a specific posture (as shown in the attached drawings), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the technical solutions in the embodiments may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should be considered to be absent, and is not within the protection scope of the invention.
It is easy to understand that the aero-engine tail jet flow field is a high-temperature and high-speed combustion flow field, wherein the type and the quantity of particles in the flow field reflect the health state of an aero-engine gas circuit. However, due to high temperature and high speed, particles are difficult to capture to carry out excitation of atomic spectrum, and further, the realization difficulty of state monitoring of the aircraft engine aiming at particle foreign matters in the jet flow field of the aircraft engine tail is high
In order to solve the problem, various embodiments of the method and the device for capturing the particulate foreign matters in the tail jet flow field of the aircraft engine are provided. According to the method and the device for capturing the particle foreign matter in the tail jet flow field of the aero-engine, the position of the diffraction-free light trap is regulated, the particles in the tail jet of the aero-engine are gradually pushed to the tail jet side under the constraint action of the diffraction-free light trap, the collection of the particles in the tail jet of the aero-engine is realized, and the technical problem that the realization difficulty of the state monitoring of the aero-engine aiming at the particle foreign matter in the tail jet flow field of the aero-engine is high at present is solved.
Referring to fig. 1, fig. 1 is a schematic diagram of an optical trap device for particulate foreign matter in a tail jet flow field of an aircraft engine according to an embodiment of the present invention.
The embodiment provides an aeroengine tail spouts flow field particulate matter light trap trapping apparatus, and the device includes:
(1) A laser: the laser emits parallel laser with certain energy to provide energy for an optical trap required by particle confinement in a jet flow field at the tail of the aeroengine.
(2) An Axicon lens: the Axicon lens generates the parallel laser emitted by the laser into the non-diffraction light beam, the parameters of the non-diffraction light beam and the parameters of the Axicon lens correspond to the formula (1) and the formula (2), the formed non-diffraction laser beam can better realize laser aggregation to form an optical trap, fine particles in an optical field are better restrained at the optical trap by light pressure, and the position of the non-diffraction light beam is changed to enable the particles to move along with the non-diffraction optical trap.
The light beam passes through the air to the Axicon lens and then passes through the air, and the vertex of the Axicon lens starts from the maximum diffraction-free area z on the optical axis max Comprises the following steps:
z max ＝R·[cotη 3 -tanθ] (1)
the two equations can be approximately simplified to:
η 3 ＝(n-1)θ；
z max ≈Rcot[(n-1)θ]。
(3) An optical lens group: the zoom lens group is composed of a lens A and a lens B, after the non-diffraction laser beam passes through the lens group, the parameters of the non-diffraction laser beam are regulated and controlled by the parameters of the lens group, the parameters comprise the position where the non-diffraction laser beam appears, the regulation and control corresponding relation of the zoom lens group to the non-diffraction laser beam is as shown in the formula (2), meanwhile, the relative position of the lens group can be controlled in a continuous motion mode, namely, the lens B of the lens group can be continuously moved relative to the lens A.
l 2 ＝f 2 (f 1 2 +f 1 f 2 -f 2 l 1 )/f 1 2 (2)
It is easy to understand, in this embodiment, the principle of trapping particulate foreign matter in the jet flow field at the tail of the aircraft engine specifically is:
firstly, a laser emits parallel laser and irradiates the parallel laser on an Axicon lens, and the parallel laser beam forms a non-diffraction beam after passing through the Axicon lens; the non-diffraction light beams irradiate on the zoom lens group, the zoom lens group is composed of a lens A and a lens B, the non-diffraction light beams form adjusted and controlled non-diffraction light beams under the action of the zoom lens group, the adjustment and control influence of the zoom lens group on the non-diffraction light beams corresponds to the fact that particles appear in a tail jet flow field of an aircraft engine, the adjusted and controlled non-diffraction light beams form light traps for the particles, and the particles are constrained in the distance zoom lens group l 2 Then, by changing the internal parameters of the zoom lens group, the pair l is formed 2 And the change of the position realizes the capture control of the particles in the flow field of the aero-engine based on the principle.
The principle of Axicon lenses producing a non-diffracted beam: when the laser emits parallel laser to irradiate the Axicon lens by plane waves vertically and at a certain angle, the method specifically comprises the following steps:
(1) The parallel laser beam emitted by the laser is vertically (eta = 0) irradiated on the incidence surface of the Axicon lens, and as shown in fig. 3, the incident parallel laser beam is converted into a non-diffraction beam by the Axicon lens, and the corresponding relation between the laser beam and the geometrical parameter and the non-diffraction propagation distance of the Axicon lens is z max ≈Rcot[(n-1)θ]Within this range z max The beams generated by the Axicon lens all obey the non-diffraction characteristic, namely the integral distribution of the light intensity energy density in the radial direction along the center of a light spot all obeys the first zero-order Bessel function, the non-diffraction beams generated by the Axicon lens exceeding the range can be quickly attenuated, especially the intensity on the optical axis, wherein R corresponds to the radius of the Axicon lens, theta is the cone angle of the Axicon lens, and n is the refractive index of the Axicon lens.
(2) When the parallel laser beam emitted by the laser irradiates on the incidence plane of the Axicon lens at a certain angle (eta is not equal to 0), as shown in fig. 4, the characteristic of diffraction-free propagation is still obeyed in a certain range after the Axicon lens, but the distance and energy distribution of the diffraction-free propagation are influenced to a certain extent.
(3) The Axicon lens is likely to have no splitting of a diffraction light spot when the oblique laser irradiates, and in order to ensure that the energy of the central light of the diffraction-free light spot is not split and to better realize the optical trapping of particle foreign matters in a tail jet field of an aeroengine, the Axicon lens needs to ensure that an included angle between a laser and the Axicon lens meets the following constraint conditions when being installed:
wherein η corresponds to an included angle of a parallel light beam emitted by the laser irradiating an Axicon lens incident plane, wherein R corresponds to a radius of the Axicon lens, θ is a cone angle of the Axicon lens, n is a refractive index of the Axicon lens, λ is a wavelength emitted by the laser, and z is a distance in a propagation direction of a non-diffracted light beam.
(4) The non-diffraction-free zone (i.e., the refraction shadow zone) in the Axicon lens is shown in fig. 5.
In the optically geometrically shaded region of Axicon, i.e., the region where Z > Zmax, the intensity of the light therein is the diffracted intensity distribution as follows:
the light intensity in this region is a typical diffracted poisson spot, poisson diffracted spots at different propagation distances, as shown in fig. 6, although the light intensity follows the distribution of the bessel function, the intensity level of the light is different by at least 2 levels with respect to the non-diffracted region. Therefore, based on the energy distribution characteristics of the Axicon region, when the particulate matters in the tail jet of the aeroengine can form an optical trap, the particulate matters with a certain size can be fully captured.
The non-diffraction beam parameter regulation and control principle of the zoom lens group is as follows: the principle structure of the optical fiber laser is as shown in fig. 7, after laser emitted by a laser device irradiates on an Axicon lens, a generated diffraction-free light beam irradiates on a lens A, the lens A converts the diffraction-free light beam of the Axicon lens into an approximately ideal annular light source in an object space of a lens B, and the annular light source generates a diffraction-free light beam with new parameters in an image space of the lens B under the action of the lens B.
After lens B 2 The correspondence relationship is as follows,
by using the transformation characteristics of the variable focus lens group on the non-diffracted beam, the f can be adjusted by the variable focus lens group 1 /f 2 The ratio of the light beam to the light beam can realize the distance condition of the central diameter of the diffraction-free light spot and the diffraction-free propagation, and meanwhile, the light beam diffraction-free area can be integrally translated along the optical axis through the change of the parameter, so that the particle foreign matter light trap capture of the tail jet flow field of the aeroengine can be realized.
The device structure: the laser is fixedly arranged on the fixed table, has the function of parallel collimation, is adjusted by manually adjusting a knob on the laser, and is also provided with two manual fine adjustment devices with adjustable degrees of freedom, so that the adjustment of the emergent laser on a space azimuth angle can be realized in a manual adjustment mode; the relative distance between the Axicon lens and the laser is fixed through a clamp, the laser is collimated through an adjusting knob on the laser, and meanwhile, the emitting direction of the laser is perpendicular to the surface of the Axicon lens through adjustment of two fine adjusting knobs on the laser, so that the laser can vertically enter the optical surface of the Axicon lens, and the inclined incidence influence caused by parallel inclined incidence of the Axicon lens is reduced as much as possible.
In this embodiment, a device for capturing particulate matter in an aircraft engine tail jet flow field is provided, which realizes the distance regulation and control of a diffraction-free optical trap by changing parameters of a lens group, and gradually pushes particulate matters to a tail jet side under the constraint action of the diffraction-free optical trap during aircraft engine tail jet, so as to realize the collection of the particulate matters during aircraft engine tail jet.
The embodiment also provides a method for capturing the particle foreign matter optical trap in the tail jet flow field of the aircraft engine, which is used for the device for capturing the particle foreign matter optical trap in the tail jet flow field of the aircraft engine, and comprises the following steps:
parallel laser is generated through a laser, and energy required by an optical trap is provided;
generating a non-diffraction light beam by utilizing the parallel laser through an Axicon lens to obtain a light trap for capturing particle foreign matters in a tail jet flow field of the aeroengine;
and regulating and controlling the position of the non-diffraction light beam through a zoom lens group so that the light trap pushes the particle foreign matters in the tail jet flow field of the aeroengine to the tail jet side.
Other embodiments or specific implementation manners of the method for capturing the particle foreign matter in the jet flow field at the tail of the aeroengine can refer to the embodiments of the devices, and are not described herein again.
The above are only preferred embodiments of the invention, and not intended to limit the scope of the invention, and all equivalent structures or equivalent flow transformations that may be applied to the present specification and drawings, or applied directly or indirectly to other related technical fields, are included in the scope of the invention.
Claims (9)
1. The utility model provides an aeroengine tail spouts flow field particulate matter light trap trapping apparatus which characterized in that includes:
the laser is used for generating parallel laser and providing energy required by the optical trap;
the Axicon lens is used for generating a non-diffraction light beam by utilizing the parallel laser so as to obtain an optical trap for capturing particle foreign matters in a tail jet flow field of the aeroengine;
and the zoom lens group is used for regulating and controlling the position of the non-diffracted light beam so as to enable the light trap to push the particle foreign matters in the tail jet flow field of the aeroengine to the tail jet side.
2. The aircraft engine tail jet flow field particulate foreign matter optical trap device of claim 1, wherein the parameter expressions of the non-diffracted light beam and the Axicon lens are as follows:
z max ＝R·[cotη 3 -tanθ]；
wherein z is max The maximum diffraction-free region on the optical axis from the cone vertex of the Axicon lens, R is the radius of the Axicon lens, eta 3 Theta is the angle between the emergent beam and the Axicon and is the cone angle of the Axicon lens.
3. The aircraft engine tail jet flow field particulate matter optical trap capturing device of claim 1, wherein the zoom lens group comprises a lens a and a lens B, the lens a is used for converting the non-diffracted light beam generated by the Axicon lens into an annular light source in the object space of the lens B, and the lens B is used for converting the annular light source into the non-diffracted light beam with new parameters.
4. The device for capturing particulate matter in an aircraft engine tail jet flow field according to claim 3, wherein the expression of the regulation relationship between the lens A and the lens B to the non-diffracted light beams is as follows:
l 2 ＝f 2 (f 1 2 +f 1 f 2 -f 2 l 1 )/f 1 2 ；
wherein l 1 Distance from Axicon lens to lens A,/ 2 Distance of lens B to the non-diffracted beam with new parameters, f 1 Distance of lens A from annular light source, f 2 Is the distance from lens B to the annular light source.
5. The aircraft engine tail jet flow field particulate matter optical trap device of claim 3, wherein the relative position of lens A and lens B is controlled to move.
6. The device for capturing the particle foreign matter in the tail jet flow field of the aeroengine as claimed in claim 1, wherein an included angle between the laser and the Axicon lens meets the following constraint condition:
wherein eta is an included angle of a parallel light beam emitted by the laser irradiating an incidence plane of the Axicon lens, theta is a cone angle of the Axicon lens, n is a refractive index of the Axicon lens, lambda is a wavelength emitted by the laser, and z is a distance in a propagation direction of a non-diffracted light beam.
7. The optical trap device for particle foreign matter in an aircraft engine tail jet flow field according to claim 1, wherein the laser is fixed on a fixed table, and the emitting laser is adjusted in the attitude by a manual fine adjustment device with adjustable degree of freedom.
8. The optical trap device for particle foreign matter in an aircraft engine tail jet flow field according to claim 1, wherein the relative distance between the laser and the Axicon lens is fixed and adjusted by a clamp.
9. An aeroengine tail jet flow field particle foreign matter optical trap capturing method is characterized in that the method is used for the aeroengine tail jet flow field particle foreign matter optical trap capturing device according to any one of claims 1 to 8, and comprises the following steps:
parallel laser is generated through a laser, and energy required by an optical trap is provided;
generating a non-diffraction light beam by utilizing the parallel laser through an Axicon lens to obtain an optical trap for capturing particle foreign matters in a tail jet flow field of the aeroengine;
and regulating and controlling the position of the non-diffracted light beam through a zoom lens group so that the light trap pushes the particle foreign matters in the tail jet flow field of the aeroengine to the tail jet side.
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