CN113567286A - Turbine shaft engine compressor blade sand dust test device and test method - Google Patents

Turbine shaft engine compressor blade sand dust test device and test method Download PDF

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Publication number
CN113567286A
CN113567286A CN202110857166.5A CN202110857166A CN113567286A CN 113567286 A CN113567286 A CN 113567286A CN 202110857166 A CN202110857166 A CN 202110857166A CN 113567286 A CN113567286 A CN 113567286A
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test
sand
blade
dust
compressor
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赵海凤
郑益民
谢买祥
鄢骏
王立
刘坤
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Hunan Aviation Powerplant Research Institute AECC
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Hunan Aviation Powerplant Research Institute AECC
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N3/56—Investigating resistance to wear or abrasion
    • G01N3/565—Investigating resistance to wear or abrasion of granular or particulate material
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N3/02—Details
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N3/02—Details
    • G01N3/04—Chucks
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N2203/02—Details not specific for a particular testing method
    • G01N2203/04—Chucks, fixtures, jaws, holders or anvils

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  • General Health & Medical Sciences (AREA)
  • General Physics & Mathematics (AREA)
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Abstract

The invention discloses a sand and dust test device and a test method for a turbine shaft engine compressor blade, which belong to the technical field of aero-engines and comprise a working area, sand blasting equipment and sand collecting equipment, wherein the working area comprises a test area and a test bed, and the circumferential rotation of the turbine shaft engine compressor blade and the movement of gravel are equivalent to the movement of the gravel relative to the blade at a certain attack angle by utilizing the equivalence principle. The sand and dust resistance of the blades, the grids and the multistage compressor of the compressor can be checked, and the whole engine resources are not needed; the test time can be shortened by increasing the sand blasting amount and the injection speed in an equivalent acceleration mode without worrying about the influence of the increased sand swallowing amount and the injection speed on other structures of the engine.

Description

Turbine shaft engine compressor blade sand dust test device and test method
Technical Field
The invention belongs to the technical field of aero-engines, and particularly relates to a device and a method for testing sand dust of compressor blades of a turboshaft engine.
Background
The turboshaft engine is used as a power device of a helicopter, and when the helicopter flies in a low airspace and close to the ground, the engine easily sucks sand and dust in the air. Although many helicopters or engines thereof adopt an air inlet protection device for sand-dust separation at present, due to the limitations of structure, performance and the like, the sand-dust separation efficiency of the air inlet protection device is generally about 60-85%, and a lot of unseparated sand-dust is still sucked into a main runner of the engine to cause abrasion of blades of an engine compressor. Some engines are delivered to users for a certain time, and the blades are seriously abraded due to the sucked sand dust, so that the engines are returned to the factory in advance. In order to avoid the problem, in the process of developing some engines at present, a method of performing a complete machine sand-dust swallowing test on the sand-dust resistance of the engine is started to be used.
And designing and optimizing the compressor blades according to the abrasion degree of the compressor blades after the whole engine swallows the sand dust test. After the design of the blades of the air compressor is optimized, a complete machine sand-dust swallowing test is carried out, repeated iteration is carried out, the design period is long, and the test cost is high. Therefore, a method is urgently needed to be found, which can be used for verifying the dust resistance of the blades of the air compressor before the complete machine carries out a dust swallowing test, so that the consumption of the complete machine resources of the engine is reduced, the development period is shortened, and the development cost is saved.
Disclosure of Invention
Aiming at the defects and shortcomings of the prior art, the invention aims to provide a device and a method for testing the sand dust of the blades of the compressor of the turboshaft engine. The sand and dust test device for the compressor blade of the turboshaft engine is utilized to realize the effect of the sand and dust test of the complete machine on the compressor blade of the turboshaft engine in a mode of spraying sand and dust to a relatively static blade test piece.
According to one aspect of the invention, the sand dust test device for the blades of the compressor of the turboshaft engine comprises a working area, sand blasting equipment and sand collecting equipment, wherein the working area comprises a test area and a test bed;
the test area consists of a test table board and a test cabin body, the test table board and the test cabin body jointly form a hollow channel, and at least one blade test piece can be arranged in the channel and allows gravel to pass through. The channel has an inlet for gravel injection; there is an outlet for grit from the test zone to perform the test. The test cabin body is made of transparent materials, the structure inside the hollow channel can be clearly observed visually, and the condition of the internal blade test piece can be observed in the test process. The test table top and the test cabin body can be separated, and personnel or tools can enter the hollow channel to complete the cleaning of the test area, the installation of the blade test piece and the like. The test table top is a plane, a test piece clamping device capable of rotating around a shaft parallel to the inlet of the test area is arranged on the inner side of the hollow channel, and the blade test piece can be fixed on the test piece clamping device and rotates around the shaft parallel to the inlet of the test area along with the test piece clamping device.
The test bed is located below the test area and used for supporting the test area. The test bed is of a hollow structure formed by the wall surface of the test bed and the top of the test bed, and the top of the test bed are an upper surface and a lower surface of the same structure. An operation table is arranged on the wall surface of the test bed, and an operation rod is arranged on the operation table. The hollow structure is internally provided with a transmission mechanism, one end of the transmission mechanism is connected with the test piece clamping device, the other end of the transmission mechanism is connected with the operating rod, and the transmission mechanism can convert the movement of the operating rod into the rotation of the test piece clamping device around a shaft parallel to the inlet of the test area, so that the angle alpha of the blade test piece relative to the gravel spraying direction is changed. At least one operation window is arranged on the wall surface of the test bed, and personnel or tools can enter the hollow structure jointly formed by the wall surface of the test bed and the top of the test bed through the operation window to complete the installation of the blade test piece, the maintenance of the transmission mechanism and other work.
The sand blasting equipment is connected with an inlet of the test area and can uniformly spray specified sand grains to the test area according to the given spraying speed v sand and the given sand blasting amount g sand.
The sand collecting equipment is connected with the outlet of the test area, can collect the sand from the test area to finish the test, and protects personnel, environment and equipment from being damaged by the sand.
The test method comprises the following steps: before the test, the sand blasting speed v sand and the sand blasting amount g sand required by the blade test piece are calculated according to the sand swallowing condition of the whole engine, and sand blasting equipment is set to spray gravel to the test area according to the requirement. According to an equivalent principle, the relative motion of the gravel under the condition that the whole engine swallows the sand and the blades of the compressor of the turboshaft engine is synthesized into the motion between the relatively static blade test piece and the gravel, and the corresponding gravel attack angle alpha is calculated. The angle alpha of the blade test piece and the gravel injection is set through a transmission mechanism by adjusting an operating rod arranged on an operating platform of the test bed.
And (3) starting the sand blasting equipment, spraying sand from the sand blasting equipment, entering the test area from the test area inlet, discharging the sand out of the test area from the test area outlet after the sand enters the sand collecting equipment connected with the test area outlet after the sand interacts with the blade test piece, and completing the recovery.
After the same time as the whole machine sand-dust swallowing test or the equivalent test time is reduced, the influence of the whole machine sand-dust swallowing test on the compressor blade of the turboshaft engine can be simulated, and the sand-dust resistance of the compressor blade is verified.
Furthermore, the transmission mechanism can realize synchronous rotation or independent rotation of the plurality of blade test pieces in a gear set, a lead screw, a connecting rod and other modes.
Furthermore, a plurality of blade test pieces in different states are arranged on the test table side by side, the spacing distance of each blade test piece is reasonably set, and each blade test piece independently rotates according to a corresponding rule through a transmission mechanism, so that the aim of simultaneously carrying out a plurality of groups of air compressor blade sand dust tests is fulfilled.
Furthermore, a plurality of blade test pieces in the same state are arranged on the test table side by side, the spacing distance of each blade test piece is reasonably set, and each blade test piece synchronously rotates through a transmission mechanism to perform a leaf sand dust test.
Furthermore, through set up multirow blade test piece on the test table face, the interval distance of each row of blade test piece is rationally set up, makes each blade test piece of same row rotate in step through drive mechanism, and different rows of blade test pieces rotate according to corresponding law alone, carry out multistage compressor dust test.
Furthermore, the model of the test cabin body is changed, so that the flow channel of the air compressor under the state of the whole machine can be simulated, and the test precision is improved.
Furthermore, a video camera and a camera are arranged outside the test cabin body, so that the whole test process can be recorded.
Furthermore, an automatic control device is additionally arranged on the control lever, the attack angle alpha of the blade test piece is adjusted according to a certain rule, and meanwhile, sand blasting equipment is arranged to adjust the sand blasting speed v sand and the sand blasting amount g sand according to the corresponding matching rule, so that an automatic test is realized.
Further, the test time can be shortened by increasing the injection speed v sand and the given injection amount g sand without worrying about the influence on other structures of the engine on the premise that the test device allows.
Compared with the prior art, the invention has the beneficial effects that:
1. by adopting the sand dust test device and the test method for the blades of the compressor of the turboshaft engine, the blade test piece is fixed on the test piece clamping device in the working area, the sand blasting equipment sprays a certain speed and a certain amount of sand to the blade test piece in the working area, the circumferential rotation of the blades of the compressor of the turboshaft engine and the movement of the sand are equivalent to the movement of the sand relative to the blades at a certain attack angle by utilizing an equivalent principle, and the sand dust resistance of the blades, the blades and the multistage compressor of the compressor can be checked without the whole engine resource.
2. By adopting the device and the method for testing the sand dust of the compressor blade of the turboshaft engine, provided by the invention, an equivalent acceleration mode can be adopted, the test time can be shortened by increasing the sand blasting amount and the injection speed, and the influence of the increase of the sand swallowing amount and the injection speed on other structures of the engine is not worried.
3. By adopting the device and the method for testing the sand dust of the blades of the compressor of the turboshaft engine, provided by the invention, a plurality of blade test pieces can be tested at the same time, the development period is shortened, and the development cost is saved.
4. By adopting the device and the method for testing the sand dust of the blades of the compressor of the turboshaft engine, the state of a blade test piece can be observed in real time, and the abrasion test data of the blades which are difficult to collect or can not be collected in the whole machine test can be collected.
5. By adopting the test device and the test method for the blade sand dust of the compressor of the turboshaft engine, the angle of the blade test piece can be adjusted through the transmission mechanism arranged at the bottom of the test piece clamping device, so that the angle of sand impacting the blade test piece can be adjusted.
Drawings
In order to facilitate understanding for those skilled in the art, the present invention will be further described with reference to the accompanying drawings.
FIG. 1 is a schematic diagram of a working area structure of a compressor blade sand dust test device of the present invention;
FIG. 2 is a schematic structural view of a test piece clamping device according to the present invention;
FIG. 3 is a schematic view of the transmission mechanism of the present invention;
FIG. 4 is a schematic diagram of a compressor blade dust test apparatus according to the present invention.
In the figure: 100. a working area; 110. a test zone; 111. a test area inlet; 112. a test zone outlet; 113. testing the cabin; 114. a test table; 115. a circular through hole; 116. installing edges;
120. a test bed; 121. an operation table; 122. an operating lever; 123. an operating window; 124. the wall surface of the test bed; 125. the top of the test bed;
130. a transmission mechanism; 131. a driven bevel gear; 132. a drive bevel gear; 133. a connecting shaft; 134. mounting a through hole; 135. defining a pin-engaging slot;
140. a blade test piece; 150. a test piece clamping device; 151. a circular mounting plate; 152. a cylindrical surface; 153. a stopper pin; 154. a threaded rod; 155. a nut;
200. a sand blasting device; 300. sand collecting equipment.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention are further described in detail below by way of examples with reference to the accompanying drawings. In the specification, the same or similar reference numerals denote the same or similar components. The following description of the embodiments of the present invention with reference to the accompanying drawings is intended to explain the general inventive concept of the present invention and should not be construed as limiting the invention.
Furthermore, in the following detailed description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the embodiments of the disclosure. It may be evident, however, that one or more embodiments may be practiced without these specific details. In other instances, well-known structures and devices are shown in schematic form in order to simplify the drawing.
Referring to fig. 1 to 4, according to a general technical concept of the present invention, a preferred embodiment of the present invention discloses a device and a method for testing sand dust of a turbine shaft engine compressor blade, the specific technical solution is as follows:
the sand and dust test device for the compressor blade of the turboshaft engine is shown in figure 1 and comprises a working area 100, sand blasting equipment 200 and sand collecting equipment 300, wherein the working area 100 is shown in figure 2 and comprises a test area 110 and a test bed 120;
the test area 110 is composed of a test table 114 and a test cabin 113, the test table 114 and the test cabin 113 together form a hollow channel, at least one blade test piece 140 can be arranged in the channel, and gravel can pass through the channel. The channel has an inlet for gravel injection, designated test zone inlet 111; there is an outlet for sand used to perform the test to exit the test zone 110, referred to as the test zone outlet 112. The test chamber 113 is made of transparent material, so that the structure inside the hollow channel can be clearly observed visually, and the condition of the internal blade test piece 140 can be observed in the test process. The test table 114 and the test chamber 113 can be separated, and personnel or tools can enter the hollow channel to complete the cleaning of the test area 110 and the installation of the blade test piece 140. The test table 114 is a flat surface, and a circular through hole 115 is provided near the inner side of the hollow passage, and a mounting edge 116 is provided near the inner side of the hollow passage.
The blade test piece 140 is fixed on the test piece clamping device 150 through threads, welding and the like, and can move together with the test piece clamping device 150. The test piece clamping device 150 is provided with a circular mounting plate 151, a cylindrical surface 152, a stop pin 153, a threaded rod 154 and a nut 155. The circular mounting plate 151 cooperates with the mounting edge 116 to define the position of the test piece holder 150 on the test table 114. Cylindrical surface 152 cooperates with circular through hole 115 to allow test piece holder 150 to rotate on test table 114 about an axis parallel to test area inlet 111.
The test bed 120 is located below the test zone 110 and supports the test zone 110. The test bed 120 is a hollow structure formed by a test bed wall surface 124 and a test bed top 125, and the test bed top 125 and the test bed top 114 are two upper and lower surfaces of the same structure. The test bed wall surface 124 is provided with an operation bed 121, and the operation rod 122 is provided on the operation bed 121. A transmission mechanism 130 is provided in the hollow structure.
The transmission mechanism 130 comprises a driven bevel gear 131, a drive bevel gear 132 and a connecting shaft 133.
The driven bevel gear 131 is arranged in a hollow structure and can rotate around the axis of the hollow structure, an installation through hole 134 and a limiting pin matching groove 135 are formed in the driven bevel gear 131, a threaded rod 154 can penetrate through the installation through hole 134, a nut 155 is matched with the threaded rod 154 to fix the test piece clamping device 150 on the driven bevel gear 131, and a limiting pin 153 is matched with the limiting pin matching groove 135 to transmit the rotation of the driven bevel gear 131 to the test piece clamping device 150.
The drive bevel gear 132 is installed in a hollow structure, and is rotatable about its axis to be engaged with the driven bevel gear 131, thereby transmitting the rotation of the drive bevel gear 132 to the driven bevel gear 131.
The connecting shaft 133 is installed in the hollow structure to be rotatable around its axis, and has one end connected to the operating lever 122 and the other end connected to the drive bevel gear 132 to transmit the rotation of the operating lever 122 to the drive bevel gear 132.
The rotation of the operating rod 122 is finally transmitted to the test piece clamping device 150 and finally transmitted to the blade test piece 140 through the transmission mechanism 130, so that the movement of the operating rod 122 is converted into the rotation of the test piece clamping device 150 around the axis parallel to the test area inlet 111 through the transmission mechanism 130, and the angle alpha of the blade test piece 140 relative to the gravel spraying direction is changed.
At least one operation window 123 is arranged on the test bed wall surface 124, and personnel or tools can enter the hollow structure formed by the test bed wall surface 124 and the test bed top 125 through the operation window 123 to complete the installation of the blade test piece 140, the overhaul of the transmission mechanism 130 and the like.
The blasting apparatus 200 is connected to the test zone inlet 111 and is capable of spraying at a given speed vSandGiven blasting amount gSandThe designated sand is uniformly sprayed toward the test area 110.
The sand trap 300 is connected to the test area outlet 112 and is capable of collecting sand from the test area 110 to protect personnel, environment and equipment from being damaged by the sand.
The invention discloses a method for testing sand dust of a compressor blade of a turboshaft engine, which comprises the following steps:
s1, before testing, calculating the sand blasting speed v required by the blade test piece 140 according to the sand swallowing condition of the whole engineSandAnd blasting amount gSandAnd the blasting apparatus 200 is set to blast grit as required toward the test zone 110. According to the equivalent principle, the relative motion of the gravel under the condition that the whole engine swallows the sand and the blades of the compressor of the turboshaft engine is synthesized into the motion between the blade test piece 140 which is relatively static and the gravel, and the corresponding gravel attack angle alpha is calculated. The angle α of the blade test piece 140 to the grit spray is set via the transmission mechanism 130 by adjusting the operation lever 122 provided on the operation table 121 of the test table 120.
And S2, starting the sand blasting equipment 200, and ejecting sand from the sand blasting equipment 200, entering the test area 110 through the test area inlet 111, discharging the sand out of the test area 110 from the test area outlet 112 after interacting with the blade test piece 140, and entering the sand collecting equipment 300 connected with the test area outlet 112 to finish recovery.
S3, after the same time as the whole machine sand-dust swallowing test is carried out or the equivalent test time is reduced, the influence of the whole machine sand-dust swallowing test on the compressor blade of the turboshaft engine can be simulated, and the sand-dust resistance of the compressor blade is verified.
In this embodiment, the transmission mechanism 130 may implement synchronous rotation or independent rotation of the plurality of blade test pieces 140 through a gear set, a lead screw, a connecting rod, and the like.
In this embodiment, a plurality of blade test pieces 140 in different states are arranged on the test table 114 side by side, the spacing distance of each blade test piece 140 is reasonably set, and each blade test piece 140 is independently rotated according to a corresponding rule through the transmission mechanism 130, so that the purpose of simultaneously performing a plurality of sets of compressor blade dust tests is achieved.
In this embodiment, a plurality of blade testers 140 in the same state are arranged on the test table 114 side by side, the spacing distance of each blade tester 140 is reasonably set, and each blade tester 140 synchronously rotates through the transmission mechanism 130 to perform the leaf sand test.
In this embodiment, the test table 114 is provided with a plurality of rows of blade test pieces 140, the spacing distance between the rows of blade test pieces 140 is reasonably set, the same row of blade test pieces 140 synchronously rotate through the transmission mechanism 130, and the different rows of blade test pieces 140 independently rotate according to the corresponding rules to perform the multistage compressor dust test.
In this embodiment, the model of the test cabin 113 is changed to simulate the compressor flow channel in the complete machine state, thereby improving the test precision.
In this embodiment, a video camera and a camera are arranged outside the test cabin 113, so that the whole test process can be recorded.
In this embodiment, the operating rod 122 is provided with an automatic control deviceAdjusting the attack angle alpha of the blade test piece 140 according to a certain rule, and simultaneously setting the sand blasting equipment 200 to adjust the sand blasting speed v according to the corresponding matching ruleSandAnd blasting amount gSandAnd automatic test is realized.
In this embodiment, the injection velocity v is increased as allowed by the test apparatusSandAnd a given blast volume gSandThe test time can be shortened without worrying about the influence on other structures of the engine.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are only exemplary embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (7)

1. A turbine shaft engine compressor blade sand dust test device comprises a sand blasting device (200), a sand collecting device (300) and a working area (100), and is characterized in that the working area (100) consists of a test area (110) and a test bed (120), the test area (110) is arranged above the test bed (120), the test area (110) consists of a test table top (114) and a test cabin body (113), the test table top (114) and the test cabin body (113) jointly form a hollow channel, at least one blade test piece (140) is arranged in the channel and allows sand to pass through, a test area inlet (111) is arranged at the front end of the channel and used for spraying sand, and a test area outlet (112) is arranged at the rear end of the channel and used for discharging the tested sand out of the test area (110);
the testing table top (114) is provided with a testing piece clamping device (150) penetrating through the testing table top and used for fixing the blade testing piece (140), the testing piece clamping device (150) is fixedly connected with a transmission mechanism (130), and the blade testing piece (140) synchronously rotates along with the testing piece clamping device (150);
the sand blasting equipment (200) is connected with the test area inlet (111), and the sand collecting equipment (300) is connected with the test area outlet (112).
2. The sand and dust test device for the compressor blades of the turboshaft engine according to claim 1, wherein the test table top (114) and the test cabin (113) are of a split structure, the test table top (114) is a plane, the test table top (114) is provided with a circular through hole (115), and one side, close to the passage, of the circular through hole (115) is provided with a mounting edge (116).
3. The sand and dust test device for the compressor blades of the turboshaft engine according to claim 2, wherein the test piece clamping device (150) comprises a circular mounting plate (151), a cylindrical surface (152), a stop pin (153), a threaded rod (154) and a nut (155), the circular mounting plate (151) is in clearance fit with the mounting edge (116), the cylindrical surface (152) is in clearance fit with the circular through hole (115), and the test piece clamping device (150) rotates on the test table top (114) around an axis parallel to the test area inlet (111).
4. The sand and dust test device for the compressor blade of the turboshaft engine according to claim 3, wherein the test bed wall surface (124) and the test bed top (125) of the test bed (120) jointly form a hollow structure, a transmission mechanism (130) is arranged in the hollow structure, the test bed top (125) and the test bed top (114) are an upper surface and a lower surface of the same structure, at least one operation window (123) is arranged on the test bed wall surface (124), the test bed wall surface (124) is provided with an operation bed (121), and the operation bed (121) is rotatably connected with an operation rod (122).
5. The sand and dust test device for the blades of the turboshaft engine compressor, according to claim 4, wherein the transmission mechanism (130) comprises a driven bevel gear (131), a driving bevel gear (132) and a connecting shaft (133), the driven bevel gear (131) is provided with a mounting through hole (134) and a limiting pin matching groove (135), the threaded rod (154) penetrates through the mounting through hole (134), a nut (155) is in threaded connection with the threaded rod (154), a limiting pin (153) is matched with the limiting pin matching groove (135), the driving bevel gear (132) is meshed with the driven bevel gear (131), one end of the connecting shaft (133) is fixedly connected with the driving bevel gear (132), and the other end of the connecting shaft (133) is fixedly connected with the operating rod (122).
6. The device for testing the sand dust of the compressor blades of the turboshaft engine according to claim 1, characterized in that the test chamber (113) is made of transparent material.
7. A sand dust test method for a compressor blade of a turboshaft engine is characterized by comprising the following steps:
s1, before testing, calculating the sand blasting speed v required by the blade test piece (140) according to the sand swallowing condition of the whole engineSandAnd blasting amount gSandSetting a sand blasting device (200) to spray gravel to a test area (110) according to requirements, synthesizing the relative motion of the gravel under the condition that the whole engine swallows the sand and a turbo shaft engine compressor blade into the motion between a relatively static blade test piece (140) and the gravel according to an equivalent principle, calculating a corresponding gravel attack angle alpha, and setting the angle alpha of the blade test piece (140) and the gravel spray through a transmission mechanism (130) by adjusting an operating rod (122) arranged on an operating platform (121) of a test platform (120);
s2, starting the sand blasting equipment (200), ejecting sand from the sand blasting equipment (200), entering the test area (110) from the test area inlet (111), discharging the sand out of the test area (110) from the test area outlet (112) after interacting with the blade test piece (140), and entering the sand collecting equipment (300) connected with the test area outlet (112) to finish recovery;
s3, after the same time as the whole machine sand-dust swallowing test is carried out or the equivalent test time is reduced, the influence of the whole machine sand-dust swallowing test on the compressor blade of the turboshaft engine can be simulated, and the sand-dust resistance of the compressor blade is verified.
CN202110857166.5A 2021-07-28 2021-07-28 Turbine shaft engine compressor blade sand dust test device and test method Pending CN113567286A (en)

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