CN113883098A - Stator blade distortion-resistant axial flow compressor and stator blade distortion-resistant method of axial flow compressor - Google Patents
Stator blade distortion-resistant axial flow compressor and stator blade distortion-resistant method of axial flow compressor Download PDFInfo
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
- F04D29/544—Blade shapes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
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Abstract
The invention provides a static blade distortion-resistant axial flow compressor and a static blade distortion-resistant method of the axial flow compressor. In the design, the static blades of the static blade axial flow compressor are distributed in a non-uniform manner, the blade grid consistency is increased in a static blade area affected by the intake distortion fluid, the original static blade consistency of other areas is not changed, the purpose of regulating and controlling a non-uniform flow field by using the non-uniformly distributed static blades is realized, the performance (flow, pressure ratio, efficiency and the like) of the compressor is ensured not to be changed under the condition of uniform incoming flow, and meanwhile, the pneumatic performance and stability margin under the condition of intake distortion are improved.
Description
Technical Field
The invention belongs to the field of production of axial-flow compressors, and particularly relates to a static blade distortion-resistant axial-flow compressor and a static blade distortion-resistant method of the axial-flow compressor.
Background
In the traditional axial-flow compressor design method, the inlet of the compressor is assumed to be uniform air inlet, namely, the inflow aerodynamic parameters and the structural load are uniform, so that the stationary blades in the axial-flow compressor are uniformly arranged, and the corresponding consistency is a certain value. Emerging boundary layer suction propulsion Systems (BLIs) have great potential in reducing aircraft drag, reducing engine power requirements, and the like. BLI propulsion systems often employ submerged S-shaped air intakes, and the air intakes, engines, are mounted at the rear of the wing or fuselage to draw as much of the boundary layer as possible. The layout mode enables the engine to continuously suck a large amount of boundary layers (low-energy fluid) under normal working conditions, airflow is easier to separate in the air inlet channel under the same inverse pressure gradient, so that air inlet distortion is continuously generated at a fixed position in the air inlet channel, and the distorted flow field enters the core machine after being transmitted by the fan, so that the work of the air compressor is further influenced.
The intake distortion changes the original design condition of the compressor, destroys the axial symmetric flow of the airflow, causes the increase of the load of the local stationary blade, causes the reduction of the stability margin and the performance deterioration of the compressor if the load is light, and causes the stall and surge of the compressor if the load is heavy, thus seriously affecting the normal work of the whole engine.
Research shows that the inlet distortion causes the flow field in the compressor to present obvious non-uniformity, after the distorted fluid is transmitted to the stationary blade through the movable blade, the load of the local stationary blade is increased, serious flow separation is generated in the flow channel, and the flow separation is only concentrated in the stationary blade flow channel affected by the distorted fluid. For boundary layer suction propulsion systems, the distortion zone transmitted to the vanes via the blades is fixed, i.e. the number and position of the passages affected by the distortion of the vanes can be determined.
Disclosure of Invention
In view of this, the present invention is directed to provide a stationary blade anti-distortion axial compressor and a stationary blade anti-distortion method for an axial compressor, so as to improve the stability and anti-distortion capability of the axial compressor and ensure the stable operation of an aircraft engine power system.
In order to achieve the purpose, the technical scheme of the invention is realized as follows:
the blade grid consistency of the static blade undistorted region of the compressor is the original consistency, and the blade grid consistency of the static blade undistorted region of the compressor is greater than that of the non-distorted region of the compressor.
Further, the structure for realizing that the consistency of the blade cascade in the stator blade distortion area of the gas compressor is greater than that of the blade cascade in the non-distortion area is as follows: the chord length of the stator blade in the distortion area is the original design chord length, and the number of the stator blades in the distortion area is increased.
Further, the structure for realizing that the consistency of the blade cascade in the stator blade distortion area of the gas compressor is greater than that of the blade cascade in the non-distortion area is as follows: the number of the stator blades in the distortion area is the original design number of the stator blades in the distortion area, and the chord length of the stator blades in the distortion area is larger than the original design chord length.
Further, a vane distortion zone vane profile is modified, the distortion zone vane inlet geometry angle matching the position vane inlet flow angle.
Compared with the prior art, the stator blade distortion-resistant axial flow compressor has the following advantages:
(1) in the design, the consistencies of the static blade distortion area and the non-distortion area are different, the consistency of the blade cascade of the non-distortion area is kept unchanged from the original consistency, the consistency of the blade cascade of the static blade distortion area influenced by the air inlet distortion fluid is increased from the original consistency, the consistency of original static blade blades of other areas is not changed, the purpose of regulating and controlling a non-uniform flow field by utilizing the non-uniformly arranged static blades is realized, and the pneumatic performance and the stability margin under the air inlet distortion condition are improved.
(2) In the design, the consistency of the blade cascade of the compressor is non-uniformly set, the design can inhibit the movable blades from being damaged due to resonance, and the non-uniformly set consistency arrangement can change the frequency of the wake of the upstream rotor sweeping the stationary blade, so that the noise reduction effect can be realized, and the operation stability of the compressor is ensured.
A static blade distortion-resisting method of an axial flow compressor comprises the following steps:
s1: determining pressure transfer change and particle transfer change of the compressor;
s2: determining a static blade distortion area of the compressor;
s3: and (3) keeping the consistency of the blade cascade in the non-distorted area of the static blade of the compressor unchanged from the original consistency, and adjusting the consistency of the blade cascade in the distorted area of the static blade to ensure that the consistency of the blade cascade in the distorted area of the static blade is greater than that of the blade cascade in the non-distorted area of the static blade.
Further, the method for increasing the consistency of the blade cascade in the stator blade distortion area of the compressor comprises the following steps: the chord length of the stator blade in the distortion area is kept unchanged as the original design chord length, and the number of the stator blades in the distortion area is increased.
Further, the method for increasing the consistency of the blade cascade in the stator blade distortion area of the compressor comprises the following steps: the number of the stator blades in the distortion area is kept unchanged from the original design number of the blades in the distortion area, and the chord length of the stator blades in the distortion area is increased.
Further, the method also includes step S4: the distortive region stationary blade profile is altered such that a stationary blade distortive region stationary blade inlet geometric angle matches the position stationary blade inlet flow angle.
Compared with the prior art, the static blade distortion resisting method of the axial flow compressor has the following advantages:
(1) in the design, the position of a stator blade distortion area is judged firstly, then the consistency of a blade cascade of the distortion area is increased, the consistency of a non-distortion area keeps unchanged from the original consistency, namely the consistency of the blade cascade of the distortion area is greater than that of the blade cascade of the non-distortion area, the purpose of regulating and controlling a non-uniform flow field by using non-uniformly arranged stator blades is realized, and the pneumatic performance and the stability margin under the condition of intake distortion are improved.
(2) In the design, the consistency of the blade cascade of the gas compressor is non-uniformly set, the attack angle of the separation of the airflow is delayed, the flow separation in the static blade flow channel in the distortion area is weakened, the damage of the movable blade due to resonance is effectively inhibited, meanwhile, the frequency of the wake of an upstream rotor sweeping the static blade can be changed by the non-uniformly set consistency arrangement, the noise reduction effect can be achieved, and the running stability of the gas compressor is ensured.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate an embodiment of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a main view of a stationary blade distortion-resistant axial compressor according to the present embodiment;
FIG. 2 is a comparison graph of distribution of front and rear stationary blades with increased consistency in a stator blade distortion region of a compressor in accordance with an embodiment;
FIG. 3 is a schematic view illustrating increasing cascade solidity by increasing the chord length of the vane in the second embodiment;
FIG. 4 is a schematic compressor vane geometry;
FIG. 5 is a comparison chart of the compressor effect before and after the consistency of the blade cascade is increased in the embodiment;
Detailed Description
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those 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 referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", "second", etc. 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 "first," "second," etc. 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 otherwise specified.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.
The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
When the compressor structure is designed, the original geometric parameters (such as chord length and number) and original consistency of the static blades can be determined through related contents in design data such as a design manual, and the original data refers to corresponding data when the inlet air of the compressor is set to be uniform and the static blades are uniformly distributed in the circumferential direction. The compressor vane geometry and parameters are shown in FIG. 4, where:
b: chord length, the length of a straight line connecting a leading edge point A and a trailing edge point B of the blade profile;
t: a compressor stator blade pitch;
β1k: the geometric angle of the blade-shaped inlet is the included angle between the tangent line of the mean camber line at the leading edge point A and the frontal line;
β1: the inlet airflow angle and the included angle between the airflow direction and the frontal line;
i: angle of attack, difference between inlet geometry angle and inlet flow angle, i.e. i ═ β1k-β1；
τ: the consistency of the leaf cascade is improved,
in order to improve the distortion resistance of the compressor, the compressor is improved as follows:
firstly, determining the position of a compressor stator blade distortion area, wherein the position is determined by the following steps:
s1: determining pressure transfer change and particle transfer change of the compressor;
the pressure transmission change is obtained by predicting through a pressure transmission formula as an expression (1), and the particle transmission change is obtained by predicting through a particle transmission formula as an expression (2):
in the formula: Δ θ pressure represents the pressure transfer variation angle, Δ θ particle represents the particle transfer variation angle, b represents the axial chord, caxRepresenting axial velocity, ω being angular velocity of blade rotation, csRepresents the speed of sound;
s2: determining a static blade distortion area of the compressor;
the circumferential influence range of the total pressure distortion of the inlet of the compressor on the static blade flow channel is determined by an equation (3), namely, a static blade distortion area of the compressor can be determined by the equation (3):
Δθst＝Δθparticle-Δθpressure+γ (3)
in the formula: Δ θ st represents a vane distortion angle, γ represents a distortion angle;
secondly, the consistency of the blade cascade in the non-distortion area of the air compressor is unchanged from the original consistency, and the consistency of the blade cascade in the distortion area is adjusted to enable the consistency of the blade cascade in the distortion area to be greater than that of the blade cascade in the non-distortion area.
The invention point of the gas compressor is that the consistency of the blade cascade in the non-distortion area of the static blade of the gas compressor is unchanged from the original consistency, and the consistency of the static blade distortion area is greater than that of the non-distortion area. At the moment, the consistency of the blade cascade of the compressor is non-uniformly arranged, the purpose of regulating and controlling a non-uniform flow field by using the non-uniformly arranged static blades is realized, the flow separation in a static blade flow channel of a distortion area is weakened, and the through-flow capacity of the compressor under the condition of intake distortion is ensured. Experiments prove that the blade grid consistency in the static blade distortion area of the compressor is increased by 10-20% compared with the original consistency, and the anti-distortion effect of the static blade distortion area of the compressor is better on the premise of ensuring smooth circulation of airflow of the compressor. For example, the consistency of the cascade in the distortion area is increased by 20%, the stability margin of the compressor under the condition that the distortion degree is 0.05 is improved by 10.07%, and the stability margin of the compressor under the condition that the distortion degree is 0.1 is improved by 18.83%. The specific value of the increment of the blade grid consistency in the static blade distortion area is determined according to the specific condition of the static blade of the compressor, which is influenced by the distortion. As shown in fig. 5, fig. 5a and 5b show the comparison curves of the flow-pressure ratio characteristic and the flow-efficiency characteristic of the prototype compressor and the non-uniform-consistency compressor under the distortion condition, respectively, wherein opt corresponds to the characteristic curve after the consistency in the distortion zone is increased by 20%, and ori corresponds to the characteristic curve before the consistency in the distortion zone is increased. From the flow-pressure ratio characteristic (shown in figure 5 a), the pressure ratio characteristic lines of the two compressors almost coincide, but the working flow range of the non-uniform-consistency compressor is enlarged by 33.9 percent relative to that of the original compressor. From the flow-efficiency characteristics (shown in fig. 5 b), the efficiency characteristics of the non-uniform-consistency compressor are higher than those of the prototype compressor. The stability margin of the prototype compressor is 8.34%, the stability margin of the non-uniform-consistency compressor is 10.20%, and the stability margin is improved by 22.30% compared with that of the prototype compressor.
The consistency of the blade cascade in the distortion area of the air compressor is greater than that of the blade cascade in the non-distortion area, and two ways are realized, as follows:
in the first embodiment, the number of the stator blades in the distortion zone is simply increased. Specifically, the method comprises the following steps: the chord length of the stator blade in the distortion area is unchanged as the original chord length, and the number of the stator blades in the distortion area is increased, so that the number of the stator blades in the distortion area is larger than the original number of the stator blades in the distortion area. The principle is that the number of the static blades in the distortion area is simply increased, at the moment, the number of the blades in the distortion area of the static blades of the compressor is larger than the original number, the pitch of the static blades in the distortion area is smaller than that of the static blades in the non-distortion area, the chord length of the blades is kept unchanged as the original chord length, according to a consistency formula, the consistency of the blade cascade in the distortion area is larger than that of the original blade cascade, and the consistency of the blade cascade in the non-distortion area is always kept unchanged as the original consistency, so that the consistency of the blade cascade in the distortion area of the static blades is larger than that of the blade cascade in the non-distortion area. As shown in fig. 1, taking an example that the blade cascade consistency of a distortion region of a compressor is increased by 20% in an angle range of-75 ° to 10 °, adjusting the number of stator blades in a distortion region from an original number of 11 to 13, and comparing the distribution of the blades before and after the increase of the number of the blades as shown in fig. 2, after the number of the stator blades is increased to 13, the pitch is reduced by 20%, and the consistency is increased by 20%.
In the second embodiment, the chord length of the stator blade in the distortion area is simply increased. Specifically, the method comprises the following steps: the number of the stator blades in the distortion area is kept unchanged as the original number of the distortion area, and the chord length of the stator blades in the distortion area is increased. As the chord length of the stator blade in the distorted region of the stator blade of the compressor is larger than the original chord length, and the number of the blades is kept unchanged, namely the blade pitch is unchanged, the blade cascade consistency in the distorted region is larger than the original consistency at the moment, and the stator blade consistency in the undistorted region is kept unchanged at the same time, so that the blade cascade consistency in the distorted region of the stator blade is larger than the blade cascade consistency in the undistorted region. As shown in FIG. 3, a specific value of the vane chord length b (b in FIG. 3)1For the original chord length of the stator blade, b2、b3Or b4Each representing a different chord length of the vane blade of the increased consistency post-distortive region) is determined from the position cascade consistency value.
In order to further improve the aerodynamic performance and stability margin of the compressor under the condition of intake distortion, the axial flow compressor changes the stator blade profile of the distortion area, so that the geometric angle of the inlet of the stator blade distortion area is matched with the airflow angle of the inlet of the stator blade at the position. In the design, the geometric angle beta of the inlet of the stator blade1kAt an angle beta to the inlet flow of the stationary blade at that position1The matching design principle is as follows: after the distorted airflow of the air compressor is transmitted to the stationary blade, in order to prevent the distorted airflow from generating serious flow separation in the stationary blade flow channel, the maximum variation range of the attack angle i of the stationary blade of the air compressor is ensured to be-2 degrees, and the optimal range is 0 degree, so the design principle of the stationary blade profile of the air compressor is to ensure the inlet geometric angle beta of the stationary blade profile of the air compressor as much as possible1kAnd inlet gas flow angle beta1And (6) matching. Tests and calculations prove that in the process of transmitting airflow to the stationary blade through the movable blade in the compressor, the inlet airflow angle beta of the stationary blade in the stationary blade distortion area1Inlet flow angle beta of the less non-distorted region stator vanes1Increase by 4-15 degrees. According to the result, in order to prevent flow separation of the flow in the flow path even if the cascade consistency τ of the vane in the distortion region is increased, the inlet geometric angle β of the vane in the distortion region is changed in the present embodiment1k' less undistorted region stationary blade inlet geometric angle beta1kIncrease 4 ~ 15 degrees, distortion zone quiet leaf import geometric angle beta1kThe specific value is determined according to the inlet airflow angle beta of the region1Determining the inlet geometry angle beta of the stator blades in the stator blade distortion zone1kAnd its corresponding inlet flow angle beta1'matching', wherein the static blade attack angle i of the distortion region is basically 0, so that the aerodynamic performance and stability margin under the intake distortion condition can be improved while the performance (flow rate, pressure ratio, efficiency and the like) of the compressor is not changed under the condition of uniform inflow.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (8)
1. A stationary blade distortion-resistant axial flow compressor is characterized in that: the consistency of the blade cascade of the non-distortion area of the static blade of the compressor is the original consistency, and the consistency of the blade cascade of the distortion area of the static blade of the compressor is greater than that of the blade cascade of the non-distortion area.
2. The vane distortion-resistant axial compressor as claimed in claim 1, wherein: the structure for realizing that the consistency of the blade cascade in the stator blade distortion area of the gas compressor is greater than that of the blade cascade in the non-distortion area is as follows: the chord length of the stator blade in the distortion area is the original design chord length, and the number of the stator blades in the distortion area is increased.
3. The vane distortion-resistant axial compressor as claimed in claim 1, wherein: the structure for realizing that the consistency of the blade cascade in the stator blade distortion area of the gas compressor is greater than that of the blade cascade in the non-distortion area is as follows: the number of the stator blades in the distortion area is the original design number of the stator blades in the distortion area, and the chord length of the stator blades in the distortion area is larger than the original design chord length.
4. The vane distortion-resistant axial compressor as claimed in claim 1, 2 or 3, wherein: changing a stationary blade distortion zone stationary blade profile, the distortion zone stationary blade inlet geometry angle matching the position stationary blade inlet flow angle.
5. The static blade distortion resisting method of the axial flow compressor is characterized by comprising the following steps: the method comprises the following steps:
s1: determining pressure transfer change and particle transfer change of the compressor;
s2: determining a static blade distortion area of the compressor;
s3: and (3) keeping the consistency of the blade cascade in the non-distorted area of the static blade of the compressor unchanged from the original consistency, and adjusting the consistency of the blade cascade in the distorted area of the static blade to ensure that the consistency of the blade cascade in the distorted area of the static blade is greater than that of the blade cascade in the non-distorted area of the static blade.
6. The axial flow compressor stator blade anti-distortion method according to claim 5, characterized in that: the method for realizing the consistency of the blade cascade in the distortion area of the air compressor is greater than that of the blade cascade in the non-distortion area comprises the following steps: the chord length of the stator blade in the distortion area is kept unchanged as the original design chord length of the stator blade, and the number of the stator blades in the distortion area is increased.
7. The axial flow compressor stator blade anti-distortion method according to claim 5, characterized in that: the method for realizing the consistency of the blade cascade in the distortion area of the air compressor is greater than that of the blade cascade in the non-distortion area comprises the following steps: the number of the stator blades in the distortion area is kept unchanged from the original design number of the blades in the distortion area, and the chord length of the stator blades in the distortion area is increased.
8. The axial flow compressor vane anti-distortion method according to claim 5, 6 or 7, characterized in that: further comprising step S4: the distortive region stationary blade profile is altered such that a stationary blade distortive region stationary blade inlet geometric angle matches the position stationary blade inlet flow angle.
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| PCT/CN2022/077487 WO2023050692A1 (en) | 2021-09-10 | 2022-02-23 | Stator vane distortion-resistant axial-flow compressor and stator vane distortion-resistant method for axial-flow compressor |
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| CN2021110667030 | 2021-09-10 | ||
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114459764A (en) * | 2022-03-10 | 2022-05-10 | 中国人民解放军空军工程大学 | Rotatable total pressure distortion generating device |
| WO2023050692A1 (en) * | 2021-09-10 | 2023-04-06 | 中国民航大学 | Stator vane distortion-resistant axial-flow compressor and stator vane distortion-resistant method for axial-flow compressor |
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- 2021-09-29 CN CN202111157706.5A patent/CN113883098A/en active Pending
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- 2022-02-23 WO PCT/CN2022/077487 patent/WO2023050692A1/en unknown
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2023050692A1 (en) * | 2021-09-10 | 2023-04-06 | 中国民航大学 | Stator vane distortion-resistant axial-flow compressor and stator vane distortion-resistant method for axial-flow compressor |
| CN114459764A (en) * | 2022-03-10 | 2022-05-10 | 中国人民解放军空军工程大学 | Rotatable total pressure distortion generating device |
| CN114459764B (en) * | 2022-03-10 | 2023-12-08 | 中国人民解放军空军工程大学 | Rotatable total pressure distortion generating device |
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| Publication number | Publication date |
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| WO2023050692A1 (en) | 2023-04-06 |
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