CN217560954U - Blade heat engine coupling test section and test system - Google Patents

Abstract

The utility model provides a blade heat engine coupling test section and test system. Wherein the test section comprises: the first cover body is provided with a through hole; the second cover body is detachably connected with the first cover body so as to form a gas channel with openings at two ends; one end of the pull rod is used for entering the gas channel through the through hole to be connected with a blade crown of the blade to be tested, the other end of the pull rod is used for being connected with the output end of the tensile machine, and a tenon of the blade to be tested is detachably arranged in a mortise of the second cover body; the sleeve is arranged at the through hole on the outer side of the first cover body and used for sleeving and sealing the pull rod; and the fixed mounting part is arranged on the outer wall surface of the first cover body and/or the second cover body and is used for fixing the position of the first cover body and/or the second cover body. The gas channel is convenient for providing a high-temperature gas environment for the blade to be tested; the pull rod is sealed through the sleeve, so that gas leakage is prevented; the fixed mounting part is convenient for applying mechanical load to the blade to be tested by using a tensile machine; the reliability and the accuracy of the test result are effectively improved.

Description

Blade heat engine coupling test section and test system

Technical Field

The utility model relates to an aeroengine field technical field, more specifically relate to a blade heat engine coupling test section and test system.

Background

With the rapid development of the modern aviation industry and the urgent need of national defense, higher and higher requirements are put forward on the performance of the aircraft engine. The turbine blade of the aero-engine bears the rapid scouring of high-temperature gas during starting and the rapid cooling during parking, and during the cycle process of starting and parking, because the temperature gradient of the blade is large, great thermal stress can be generated, so that the thermal fatigue of the blade is caused, and therefore, a thermal shock test of the turbine blade is required to be carried out, and the thermal shock resistance of the blade is checked; in addition, because the blade rotates at a high speed to generate a large centrifugal force load, and the temperature gradient and the mechanical load act together to generate the thermal mechanical coupling fatigue of the blade, the thermal mechanical coupling test of the turbine blade is required to be carried out to examine the thermal mechanical fatigue performance of the blade.

At present, the traditional turbine blade thermo-mechanical coupling fatigue test method is difficult to simulate the temperature field of the turbine blade in actual engine operation, and the reliability and accuracy of the test result are difficult to further improve. Therefore, it is necessary to provide a thermal-mechanical coupling test section and a test system for the blade.

SUMMERY OF THE UTILITY MODEL

An aspect of an embodiment of the present specification discloses a blade thermo-mechanical coupling test section, including: the first cover body is provided with a through hole; the second cover body is detachably connected with the first cover body to form a gas channel with openings at two ends; one end of the pull rod is used for entering the gas channel through the through hole to be connected with a blade crown of the blade to be tested, the other end of the pull rod is used for being connected with an output end of a tensile machine, and a tenon of the blade to be tested is detachably mounted in a mortise of the second cover body; the sleeve is arranged at the through hole at the outer side of the first cover body and used for sleeving and sealing the pull rod; and the fixed mounting part is arranged on the outer wall surface of the first cover body and/or the second cover body and is used for fixing the position of the first cover body and/or the second cover body.

In some embodiments, the fixed mounting portion is a lug formed by extending the outer wall surface of the first cover body and/or the second cover body outwards or a reinforcing rib provided with a through hole.

In some embodiments, the first cover body comprises an upper cover plate and two side wall plates connected with the upper cover plate, the second cover body comprises a lower cover plate, one end of each side wall plate is connected with the upper cover plate, the other end of each side wall plate is detachably connected with the lower cover plate so as to form a gas channel together, and the fixed mounting portions are arranged on the outer wall surfaces of the two side wall plates.

In some embodiments, the connection surfaces between the side wall plate and the lower cover plate are respectively concave-convex surfaces which are engaged with each other.

In some embodiments, pneumatic sealing channels are symmetrically arranged at positions on two sides of the sleeve, an air outlet end of each pneumatic sealing channel is communicated with the through hole, the sectional area of a gap between the surface of the pull rod and the through hole is smaller than that of the air outlet end of the pneumatic sealing channel, and the area ratio of the air outlet end to the cross area of the gap between the surface of the pull rod and the through hole is 1: s, S is greater than or equal to 10.

In some embodiments, at least one accompanying blade which is consistent with the shape and the structure of the blade to be tested is installed on the inner side of the second cover body in the transverse direction of the gas channel so as to simulate the working environment in which the blade to be tested is actually positioned.

In some embodiments, the second cover body is provided with a cold air pipeline which is respectively communicated with the inner cavity of the blade to be tested and the inner cavity of each accompanying lining blade.

In some embodiments, the end of the pull rod connected with the blade to be tested is provided with a cold air groove, and the cold air groove is communicated with the inner cavity to discharge cold air passing through the inner cavity of the blade to be tested.

In some embodiments, the accompanying lining blade and the inner wall surface of the first cover body are provided with gaps, and the gaps are communicated with the inner cavity of the accompanying lining blade.

Another aspect of the embodiments of the present specification discloses a blade heat engine coupling test system, including: the blade in any embodiment of the above is in a thermal engine coupling test section; the combustion section is connected with the blade thermal engine coupling test section to provide high-temperature fuel gas; the fuel supply system is connected with the combustion section to supply fuel; an air supply system connected to the combustion section to provide compressed air; and the cooling system is connected with the thermal engine coupling test section of the blade to provide a cooling medium.

The embodiment of the specification can at least realize the following beneficial effects:

a gas channel for testing the blade to be tested is formed by the first cover body and the second cover body, so that a high-temperature gas environment is provided for the blade to be tested; the sleeve is used for sleeving and sealing the position of the pull rod, so that the gas leakage is effectively prevented; the first cover body and/or the second cover body are/is fixed in position through the fixing and installing part, so that a tensile machine can be used for applying mechanical load to the blade to be tested conveniently, and the mechanical load applied to the blade to be tested can be detected conveniently; the thermal engine coupling state simulation method can accurately simulate the pneumatic environment of the turbine blade in the actual engine work and the thermal engine coupling state when the blade temperature, the cascade temperature and the centrifugal force load are loaded simultaneously, so that the reliability and the accuracy of the test result are effectively improved.

Drawings

FIG. 1 is a diagram illustrating an application scenario of a blade thermo-mechanical coupling test system according to some embodiments of the present disclosure.

FIG. 2 is a schematic block diagram of a blade thermo-mechanical coupling test system according to some embodiments of the present disclosure.

FIG. 3 is a schematic structural diagram of a thermal-mechanical coupling test section of a blade according to some embodiments of the present disclosure.

Fig. 4 is an exemplary assembly diagram between an upper cover panel, a side wall panel, and a lower cover panel as contemplated in some embodiments of the present disclosure.

FIG. 5 is a perspective view of a thermal-mechanical coupling test section of a blade according to some embodiments of the present disclosure.

FIG. 6 is a schematic diagram of the mating of the intake, combustion and exhaust passages involved in some embodiments of the present disclosure.

FIG. 7 is a schematic view of a blade under test according to some embodiments of the present disclosure.

Fig. 8 is a partially enlarged schematic view of a portion a of fig. 3.

Fig. 9 is a partially enlarged schematic view of a portion B in fig. 3.

Fig. 10 is a schematic diagram of a liquid cooling channel according to some embodiments of the present disclosure.

Reference numerals:

100. a blade thermal engine coupling test system; 110. a thermal engine coupling test section of the blade; 120. a combustion section; 130. an oil supply system; 140. an air supply system; 150. a cooling system; 160. an exhaust section;

210. a first cover body; 211. an upper cover plate; 212. a side wall panel; 220. a second cover body; 221. a lower cover plate; 222. a coupling wire channel; 230. a pull rod; 240. a sleeve; 241. a grate sealing structure; 250. a fixed mounting portion; 260. pneumatically sealing the channel; 270. a cold air pipeline; 280. a leaf to be tested; 281. lining the blades; 290. a gas channel;

310. an air intake passage; 320. an exhaust passage; 330. a liquid inlet pipe; 340. a liquid outlet pipe;

410. a cold air tank; 420. a through hole; 430. a gap;

510. a liquid cooling channel; 520. a honeycomb cooling structure.

Detailed Description

The technical solutions of the present specification are further described in detail below with reference to the accompanying drawings, but the scope of protection of the present specification is not limited to the following descriptions.

In order to make the objects, technical solutions and advantages of the embodiments of the present disclosure more clear, the technical solutions of the embodiments of the present disclosure will be clearly and completely described below with reference to the drawings in the embodiments of the present disclosure, and it is obvious that the described embodiments are some embodiments of the present disclosure, but not all embodiments. All other embodiments obtained by a person skilled in the art without any inventive step based on the embodiments in the present description belong to the protection scope of the present description. Thus, the following detailed description of the embodiments of the present specification, presented in the accompanying drawings, is not intended to limit the scope of the specification, as claimed, but is merely representative of selected embodiments of the specification. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments in the present specification without any creative effort belong to the protection scope of the present specification.

In the description of the present specification, it is to be understood that the terms indicating an orientation or positional relationship are based on the orientation or positional relationship shown in the drawings, and are only for convenience of describing the present specification and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus should not be construed as limiting the present specification.

In this specification, unless explicitly stated or limited otherwise, the terms "mounted," "connected," "fixed," and the like are to be construed broadly and include, for example, fixed connections, detachable connections, or integral parts; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or may be connected through the use of two elements or the interaction of two elements. The specific meanings of the above terms in the present specification can be understood by those of ordinary skill in the art as appropriate.

In this specification, unless explicitly stated or limited otherwise, the presence of a first feature above or below a second feature may include the first and second features being in direct contact, or may include the first and second features not being in direct contact but being in contact with each other by way of additional features between them. Also, the first feature may be over, above or on the second feature including the first feature being directly above or obliquely above the second feature, or simply indicating that the first feature is at a higher level than the second feature. The presence of a first feature below, beneath or below a second feature in this specification includes the presence of the first feature directly below and obliquely below the second feature or simply means that the first feature is at a lesser level than the second feature.

The present invention will be further described with reference to the following examples, which are intended to illustrate only some, but not all, of the embodiments of the present invention. Based on the embodiments in the present specification, other embodiments used by those skilled in the art without any creative work shall fall within the protection scope of the present invention.

Referring now to the drawings, wherein the showings are for the purpose of illustrating selected embodiments of the invention only, the disclosure is not limited thereto.

FIG. 1 illustrates an application scenario of a blade thermo-mechanical coupling test system 100 of some embodiments herein. FIG. 2 illustrates a schematic structural diagram of a blade thermo-mechanical coupling test system 100 of some embodiments of the present disclosure.

As shown in FIG. 1, in some application scenarios, the blade thermo-mechanical coupling test system 100 may include a blade thermo-mechanical coupling test section 110, a combustion section 120, an oil supply system 130, an air supply system 140, and a cooling system 150.

The blade thermo-mechanical coupling test section 110 is used to provide a high temperature gas environment for the blade 280 to be tested and to apply mechanical loads to the blade 280 to be tested.

In the specification, the high-temperature gas refers to gas above 1500K, and the high-temperature environment refers to an environment with the temperature above 1500K.

The combustion section 120 is used for delivering high-temperature gas to the blade heat engine coupling test section 110, and providing a high-temperature gas test environment for the blade 280 to be tested.

In some embodiments, as shown in FIG. 2, the combustion section 120 includes an electric heater and a combustion chamber, with the front end of the combustion chamber connected to the electric heater and the rear end of the combustion chamber connected to the blade thermo-engine coupling test section 110. The combustion chamber is used for specially providing high-temperature fuel gas with the temperature of more than 1500K for the blade heat engine coupling test section 110, even the temperature can reach 2000K, and the temperature cycle load test of the blade 280 to be tested is realized by adjusting the temperature of the fuel gas.

In some embodiments, a thermocouple is connected between the combustion chamber and the electric heater, and a thermocouple is connected between the combustion chamber and the blade thermo-mechanical coupling test section 110.

The oil supply system 130 is used to deliver fuel to the combustion section 120.

In some embodiments, as shown in FIG. 2, oil supply system 130 includes an aviation kerosene tank, an oil pump, a vortex shedding flowmeter, and a pressure gauge, which are in fluid communication with the aviation kerosene tank, the oil pump, the vortex shedding flowmeter, the pressure gauge, and the combustion chamber to provide kerosene to the combustion chamber.

The air supply system 140 is used to provide compressed air to the combustion chamber.

In some embodiments, as shown in fig. 2, the air supply system 140 includes an air compressor, an air tank, a main valve, a solenoid valve, a flow meter, and a pressure gauge, and the air compressor, the air tank, the main valve, the solenoid valve, the flow meter, the pressure gauge, and the electric heater are connected in sequence to provide compressed air for the electric heater.

In some embodiments, a thermocouple is connected between the flow meter and the pressure gauge.

The cooling system 150 is used to provide a cooling medium to the blade thermo-mechanical coupling test section 110.

In some embodiments, as shown in fig. 2, the cooling system 150 includes an air compressor, an air tank, a throttle valve, a refrigerator, a flow meter, and a pressure gauge, and the air compressor, the air tank, the throttle valve, the refrigerator, the flow meter, the pressure gauge, and the vane heat engine coupling test section 110 are sequentially connected to provide cold air for the vane heat engine coupling test section 110; this part corresponds to the cold air system.

In some embodiments, thermocouples are connected between the pressure gauges and the blade thermo-mechanically coupled test section 110.

In some embodiments, as shown in fig. 2, the cooling system 150 further includes a cooling water tank, a water pump, and a valve, where the cooling water tank, the water pump, the valve, and the blade heat engine coupling test section 110 are connected to form a circulating water cooling channel, so as to provide cooling water for the blade heat engine coupling test section 110; this section corresponds to a water cooling system.

In some embodiments, a PT100 temperature sensor is connected between the blade thermo-mechanical coupling test section 110 and the cooling water tank.

In some embodiments, the vane thermo-mechanical coupling test system 100 may further include an exhaust section 160, and the exhaust section 160 is used for connecting with the vane thermo-mechanical coupling test section 110 to exhaust the tested high-temperature combustion gas.

In some embodiments, as shown in fig. 2, the exhaust section 160 includes a solenoid valve and a flow-inducing fan, the vane thermo-engine coupling the test section 110, the solenoid valve and the flow-inducing fan delivering connections to remove the high temperature combustion gases after testing.

In some embodiments, the draft fan is provided with a sound deadening canopy.

In some embodiments, the thermal engine coupling testing system 100 may further include a control system, which is connected to the thermocouple, the vortex shedding flowmeter, the oil pump, the pressure gauge, the main valve, the solenoid valve, the electric heater, the air compressor, the throttle valve, the flowmeter, the water pump and the valve to control various parameters involved in the testing process, such as the flow rate and the flow velocity of the fuel oil, the flow rate and the flow velocity and the pressure of the high-temperature fuel gas, the flow rate and the flow velocity and the pressure of the cold air, the flow rate and the flow velocity and the pressure of the cooling water, and the like.

FIG. 3 is a schematic structural diagram of a blade thermo-mechanical coupling test section 110 according to some embodiments of the present disclosure. Fig. 4 is an exemplary assembly diagram between the upper cover plate 211, the side wall plate 212, and the lower cover plate 221, as contemplated in some embodiments of the present disclosure. FIG. 5 is a perspective view of a blade thermo-mechanical coupling test section 110 as contemplated in some embodiments of the present description.

As shown in FIG. 3, the blade thermo-mechanical coupling test section 110 may include a first cover 210, a second cover 220, a drawbar 230, a sleeve 240, and a fixed mount 250.

In some embodiments, the first cover 210 and the second cover 220 are detachably connected to form a gas channel 290 with two open ends.

In some embodiments, the first cover 210 includes an upper cover 211 and two side wall plates 212 connected to the upper cover 211, and the second cover 220 includes a lower cover 221, wherein one end of the two side wall plates 212 is connected to the upper cover 211, and the other end is detachably connected to the lower cover 221 to form a gas channel 290.

In some embodiments, the second cover 220 is provided with a thermocouple wire passage 222, and 2 thermocouple wires are disposed in the thermocouple wire passage 222 and are used to detect the temperatures of the end portion and the middle portion of the blade 280 to be tested, respectively.

In some embodiments, the thermocouples enter the gas channel 290 and extend to the ends and middle of the blade 280 to be tested for temperature sensing.

In some embodiments, the drawbar 230 is configured to provide a tangential force to the blade to be tested under the driving of a power source such as a tensile machine to simulate a tangential force load to the blade to be tested during rotation.

In some embodiments, the tie rod 230 and the connecting end of the blade to be tested are integrally cast, that is, the joint between the tie rod and the blade to be tested is integrally formed; the high-temperature gas is prevented from ablating the connection part of the pull rod 230 and the blade to be tested, so that the connection part is prevented from being broken.

In some embodiments, a labyrinth seal 241 is provided between the sleeve 240 and the drawbar 230 sleeved therein.

In some embodiments, the inner cavity of the sleeve 240 may be cylindrical or rectangular parallelepiped in shape. Accordingly, the labyrinth seal structure 241 has a cylindrical or rectangular solid shape as a whole.

In some embodiments, the upper cover plate 211 is welded to the two side wall plates 212, respectively, to achieve a fixed connection. In other embodiments, the top cover 211 is integrally formed with the two sidewalls 212.

In some embodiments, the connection portion of the upper cover plate 211 and the side wall plate 212 extends horizontally outward to form a flange, and the flanges are welded to each other to achieve a fixed connection.

In some embodiments, the shape of the connecting surface of the upper cover plate 211 and the side wall plate 212 may be one or more of a zigzag shape, a corrugated shape, and a rectangular shape; to minimize gas leakage.

In some embodiments, as shown in fig. 4, the connecting portion of the upper cover plate 211 and the side wall plate 212 extends horizontally and outwardly and then vertically to form a right-angled boss, and then the upper cover plate and the side wall plate are fixedly connected by welding; to minimize gas leakage.

In some embodiments, the connection points of the upper cover plate 211 and the side wall plate 212 are welded after being connected by bolts.

In some embodiments, the upper cover plate 211 is detachably connected to the two side wall plates 212 by fasteners such as bolts and nuts.

In some embodiments, the lower cover plate 221 is detachably connected to the two side wall plates 212 by fasteners such as bolts and nuts.

In some embodiments, the connection portion between the lower cover plate 221 and the sidewall plate 212 extends horizontally outward to form flanges, and the flanges are connected by bolts.

In some embodiments, as shown in fig. 4, the connection portion of the lower cover plate 221 and the sidewall plate 212 extends horizontally and outwardly and then vertically to form a right-angle boss, and the right-angle boss is connected by a bolt.

In some embodiments, the connection surfaces between the lower cover plate 221 and the side wall plate 212 are concave-convex surfaces which are engaged with each other.

In some embodiments, the relief in the relief surface is one or more combinations of a sawtooth shape, a corrugated shape, and a rectangular shape.

In some embodiments, the fixing portion 250 is used to fix the position of the first cover 210 and/or the second cover 220.

In some embodiments, the fixing portion 250 is disposed on an outer wall surface of the first cover 210 and/or the second cover 220.

In some embodiments, the fixing and mounting portion 250 is a lifting lug formed by extending the outer wall of the first cover body 210 and/or the second cover body 220 outward or a reinforcing rib provided with a through hole.

In some embodiments, the lifting lugs may be disposed on the outer wall surfaces of the two side wall plates 212, and the blade thermo-mechanical coupling test section 110 may be mounted on a mounting base (fixture) of a tensile machine through the lifting lugs, so that when the tensile machine applies a mechanical load to the blade 280 to be tested through the tie bars 230, the tensile force (mechanical load) applied to the blade 280 to be tested can be accurately detected.

In some embodiments, the fixed mount 250 is used to couple with a tensile machine to suspend the lower cover plate 221.

In some embodiments, the fixing portion 250 is configured to be detachably connected or fixedly connected to the outside to suspend the bottom cover 221.

In some embodiments, the bottom side of the lower cover 221 is provided with a connector for connecting with a tensile machine, so that the lower cover 221 is suspended.

After the lower cover plate 221 is suspended, the force applied by the tensile machine of the drawbar 230 and the tensile machine of the lower cover plate 221 can be accurately adjusted.

In some embodiments, the lower cover plate 221 thickness is at least 1.5 times greater than the height of the blade 280 to be tested, and the upper cover plate 211 thickness exceeds 0.5 times the height of the blade 280 to be tested. The upper cover plate 211 is a non-force-bearing part, but because the cascade environment is a high-temperature and high-pressure environment, the upper cover plate 211 should also keep a certain thickness to ensure a reliable structure.

The lower cover plate 221 and the upper cover plate 211 are assembled by metal plates with certain thickness. The specific thickness value is set according to actual requirements, and the design includes but is not limited to the following advantages:

the first benefit is: the thickness of the cover plate is large enough, so that the rigidity of the wall surface is large enough, and the wall surface structure of the thermal engine coupling test section 110 of the blade is difficult to damage even if the internal pressure of the blade cascade reaches 30-50 atmospheric pressures;

the second benefit is: the thermal inertia of the wall surface of the blade heat engine coupling test section 110 is large enough, so that the wall surface of the blade heat engine coupling test section 110 does not need to be cooled by water spraying during the experiment, and the strength of the blade heat engine coupling test section 110 can meet the test requirement;

a third benefit: the thermal fatigue property of the blade thermal engine coupling test section 110 can be improved, so that the service life of the blade thermal engine coupling test section 110 is far longer than that of the blade 280 to be tested, and the safety of test equipment in a fatigue test is ensured;

the fourth benefit: the rigidity of the blade thermo-engine coupling test section 110 is far greater than that of the blade 280 to be tested, so that when the blade 280 to be tested is pulled and pressed, the blade thermo-engine coupling test section 110 can still be stable, and large deformation cannot occur, so that the deformation and the load of the blade 280 to be tested are influenced.

In some embodiments, at least one accompanying blade 281 conforming to the shape and structure of the blade 280 to be tested is installed on the inner side of the second cover 220 in the transverse direction of the gas passage 290 to simulate the working environment in which the blade 280 to be tested is actually located.

Wherein, the transverse direction is a horizontal direction perpendicular or substantially perpendicular to the length direction of the drawbar 230, and the horizontal direction is perpendicular or substantially perpendicular to the direction of the gas entering the gas channel 290; substantially perpendicular means that both directions may vary within 90 ° ± 5 °; the transverse direction may refer to the directions C, D indicated by arrows in fig. 3.

In some embodiments, there are 2n accompanying blades 281 and the accompanying blades are symmetrically disposed at the left and right sides of the blade 280 to be tested. 2n refers to an integer multiple of 2, such as 2, 4, 6, 8, 10, etc.

In some embodiments, the inner side surface of the second cover 220 is circular arc-shaped. The inner side surface of the second cover 220 refers to a common mounting surface where the blade 280 to be tested and the plurality of accompanying liner blades 281 are located, so that the working environment where the blade 280 to be tested is actually located can be truly simulated, and the testing reliability is effectively improved.

In some embodiments, both the vane 280 to be tested and the accompanying vane 281 may be removably mounted to the inside of the second cover 220. The detachable connection structure can be detached in a detachable mode such as mortise and tenon connection (tenon and mortise).

In some embodiments, the second cover 220 is provided with a cold air pipeline 270, and the cold air pipeline 270 is respectively communicated with the inner cavity of the vane 280 to be tested and the inner cavity of each of the accompanying vanes 281. Wherein, the air inlet end of the cold air pipeline 270 is connected with the cold air system in the cooling system 150 to deliver cold air to the inner cavity of the blade 280 to be tested and the inner cavity of each of the accompanying blades 281. The temperature of the cold air is close to the temperature of the actual cold air of the engine, and the difference value of the temperature of the cold air and the temperature of the actual cold air is-1 ℃ or-3 ℃.

Fig. 6 is a schematic diagram of the cooperation of the intake passage 310, the combustion gas passage 290, and the exhaust passage 320 in some embodiments of the present disclosure. FIG. 7 is a schematic view of a blade 280 to be tested according to some embodiments of the present disclosure.

In some embodiments, as shown in FIG. 6, the inlet of the gas channel 290 is provided with an inlet channel 310 and the outlet of the gas channel 290 is provided with an outlet channel 320. Wherein the intake passage 310 is adapted to be connected to the combustion section 120 and the exhaust passage 320 is adapted to be connected to the exhaust section 160.

In some embodiments, the inlet passage 310 forms an angle with the axial direction of the outlet passage 320, and the through-hole 420 is located at the angle.

In some embodiments, the included angle is determined from the included angle between a tangent to one end of the mean camber line and a tangent to the other end of the mean camber line in the cross-section of the middle portion of the blade 280 being tested.

The air inlet channel 310 is connected with the blade heat engine coupling test section 110 through a flange, the air outlet channel 320 is connected with the blade heat engine coupling test section 110 through a flange, and the flow direction size of the blade heat engine coupling test section 110 can be small enough through the installation mode of the flange, the blade heat engine coupling test section 110 and the flange, so that high-temperature alloy material waste is avoided; the flow direction size of the blade thermo-mechanical coupling test section 110 is only slightly larger than the chord length of the blade 280 to be tested.

As shown in fig. 6, an arrow F is an entering direction of the high-temperature gas, an arrow E is an exhausting direction of the high-temperature gas, an included angle G is an included angle between the directions of the arrows E and F, is also an included angle formed by the axial directions of the air inlet channel 310 and the air outlet channel 320, and is also a deflection angle of the high-temperature gas after applying work to the vane 280 to be tested. The extensions of the E and F arrows may be considered tangents to the two ends of the mean camber line in the cross section of the middle portion of the blade 280 to be tested.

In practical application, the included angle G can be determined according to the specific structure and mounting position of the blade 280 to be tested and the design requirements of the above scheme; that is, the included angles G corresponding to the blades 280 to be tested with different shapes and sizes are different, and the included angles G corresponding to the blades 280 to be tested are different when the blades 280 to be tested are installed at different positions. The included angle is allowed to have an error of + -1 deg. -5 deg. when determined. In some embodiments, the included angle G may range from 20 ° to 70 °, and the specific angle may be 20 °, 25 °, 30 °, 35 °, 40 °, 45 °, 50 °, 55 °, 60 °, 65 °, 70 °. In some embodiments, the included angle G may range from 20 to 50. In some embodiments, included angle G may range from 25 to 55. In some embodiments, the included angle G may range from 30 to 60. In some embodiments, the included angle G may range from 35 to 65. In some embodiments, the included angle G may range from 40 to 70. In some embodiments, the included angle G may range from 25 to 65. In some embodiments, the included angle G may range from 30 to 60. In some embodiments, the included angle G may range from 35 to 55. In some embodiments, included angle G may range from 40 to 50.

It should be noted that, in an actual working environment, after the high-temperature gas enters the gas channel 290, the inventor finds that work is applied to the blade 280 to be tested, the work is converted into kinetic energy for rotating the blade 280 to be tested, and after the work is applied to the high-temperature gas, the flow direction of the high-temperature gas is deflected. During the test, if the included angle between the air inlet channel 310 and the air outlet channel 320 is not formed, the high-temperature gas directly impacts the inner wall of the gas channel 290 after turning, and a strong ablation effect is formed on the inner wall of the gas channel 290, so that the service life of the experimental equipment is seriously shortened, and a great safety risk and a great test cost are brought to the test.

In the above embodiment, by setting the included angle G, after the high-temperature gas impacts the blade 280 to be tested, the flow direction of the high-temperature gas deflects toward the outlet of the gas channel 290 and is discharged along the length direction of the exhaust channel 320, so that the high-temperature gas is effectively prevented from impacting the inner wall of the gas channel 290, the ablation condition of the inner wall of the gas channel 290 is greatly relieved, the service life of the gas channel 290 can be greatly prolonged, and the experimental risk and the experimental cost are effectively reduced; and the gas exhaust section 160 can be used together, so that the residence time of high-temperature gas in the gas exhaust channel 320 can be reduced, and the ablation condition of the inner wall of the gas channel 290 can be further relieved.

As shown in FIG. 7, the middle of the blade 280 to be tested refers to: the midline I between the two ends of the blade 280 to be tested in the length direction extends to the two ends to form an area H after 5% of the length of the blade 280 to be tested. In some embodiments, the middle portion of the blade 280 to be tested may particularly designate a 50% length position in the length direction of the blade 280 to be tested.

The cross-section of the middle of the blade 280 to be tested refers to: in the region H, and in a direction parallel to the length direction of the central line I, the blade 280 to be tested is profiled, and the cross section of the middle portion of the blade 280 to be tested is obtained.

The mean camber line in the cross-section of the middle portion of the blade 280 being tested refers to: in the cross section, the middle points of the two ends of the blade 280 to be tested in the width direction are used as end points, the arc direction of the blade 280 to be tested is used as an arc line, and the obtained arc line segment is the middle arc line.

The tangents to the two ends of the mean camber line in the cross section of the middle portion of the blade 280 to be tested refer to: the two ends of the mean camber line are respectively extended outwards to obtain rays which are tangent lines of the two ends of the mean camber line.

Fig. 8 is a partially enlarged schematic view of a portion a of fig. 3. Fig. 9 is a partially enlarged schematic view of a portion B in fig. 3.

In some embodiments, as shown in fig. 8, the first cover 210 is provided with a through hole 420.

In some embodiments, as shown in fig. 8, the end of the blade 280 to be tested connected to the pull rod 230 is provided with a cold air groove 410, and the cold air groove 410 is communicated with the inner cavity of the blade 280 to be tested so as to discharge cold air passing through the inner cavity of the blade 280 to be tested. Wherein, the cooling of the end of the drawbar 230 can be performed through the cooling slot 410.

In some embodiments, one end of the pull rod 230 is used to enter the gas channel 290 through the through hole 420 to connect with the tip shroud of the blade to be tested, and the other end of the pull rod 230 is used to connect with the output end of the tensile machine, wherein the tenon of the blade to be tested is detachably installed in the mortise of the second cover 220.

In some embodiments, the sleeve 240 is disposed at the through hole 420 of the outer side of the first cover 210 and performs a socket sealing on the pull rod 230.

In some embodiments, the pneumatic sealing channels 260 are symmetrically disposed at two sides of the sleeve 240, the air outlet end of the pneumatic sealing channel 260 is communicated with the through hole 420, and the air inlet end of the pneumatic sealing channel 260 is connected to the cold air system in the cooling system 150, so as to introduce air into the through hole 420, whose air pressure is slightly greater than that of the through hole 420 at the communication position with the gas channel 290, to achieve pneumatic sealing.

The pull rod 230 can be cooled and sealed through the cooperation of the pneumatic sealing channel 260 and the labyrinth sealing structure 241, the temperature in the sleeve 240 is reduced through cooling, and the high-temperature fuel gas is prevented from leaking outwards through the sleeve 240 through sealing.

Wherein, the air outlet end of the pneumatic sealing channel 260 is arranged as close as possible to the position where the through hole 420 and the fuel gas channel 290 are communicated. "slightly larger" refers in particular to: if the gas pressure of the pneumatic sealing channel 260 introduced into the through hole 420 is p1, and the gas pressure at the communication part of the through hole 420 and the gas channel 290 is p2, the value range of p1 is 1-1.05 times of p 2.

In other embodiments, the pneumatic sealing channel 260 is configured with a gas source that delivers air at ambient temperature and pressure to the pneumatic sealing channel 260. The normal-temperature high-pressure air is mixed at the communication position of the through hole 420 and the fuel gas channel 290, so that the sealing effect can be achieved, and the high-temperature fuel gas can be effectively prevented from flowing out of the through hole 420. Meanwhile, in order to ensure the pneumatic sealing effect, as shown in fig. 8, a gap between the surface of the pull rod 230 and the through hole 420 may be 0.1mm to 0.5mm, the sectional area of the gap is much smaller than that of the pneumatic sealing channel 260, and the design area ratio of the two is 1: s and S are more than or equal to 10, according to a gas continuity equation, the volume flow of the sealing gas is more than 10 times of the gas flow, the gas leakage rate can be controlled to be very small (for example, not more than 1% of the main flow gas flow), and the temperature of the leaked gas is reduced to be less than half of the temperature of the main flow gas (when the unit is centigrade, for example, 1000 centigrade is reduced to be less than 500 centigrade).

The normal temperature and high pressure air refers in particular to: air with temperature of 20-25 ℃ and air pressure of 3-3.2 MPa.

In some embodiments, as shown in fig. 9, a gap 430 is formed between the lining blade 281 and the inner wall surface of the first cover body 210, and the gap 430 is communicated with the inner cavity of the lining blade 281.

Fig. 10 is a schematic diagram of a liquid cooling channel 510 according to some embodiments of the present disclosure.

In some embodiments, the inlet channel 310 and the outlet channel 320 are provided with a liquid cooling channel 510 surrounding the respective internal cavities, the bottom side of the liquid cooling channel 510 is provided with an inlet pipe 330 (see fig. 5), the top side of the liquid cooling channel 510 is provided with an outlet pipe 340 (see fig. 5), and the liquid cooling channel 510 is connected with a water cooling system in the cooling system 150 through the inlet pipe 330 and the outlet pipe 340 to cool the inlet channel 310 and the outlet channel 320 and prevent the inlet channel 310 and the outlet channel 320 from being overloaded.

In some embodiments, as shown in FIG. 10, the cooling structure of the liquid cooling channels 510 may be a honeycomb cooling structure 520.

The above-mentioned embodiments are provided for illustration and not for limitation, and the changes of the examples and the replacement of equivalent elements should be understood as belonging to the scope of the present invention.

From the above detailed description, it will be apparent to those skilled in the art that the present invention can be embodied in other specific forms without departing from the spirit or essential attributes thereof.

While the preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. It is therefore intended that the following appended claims be interpreted as including the preferred embodiment and all such alterations and modifications as fall within the scope of the invention. The above description is only exemplary of the present invention and should not be taken as limiting, and all changes, equivalents, and improvements made within the spirit and principles of the present invention should be understood as being included in the scope of the present invention.

It should be noted that the above description of the flow is for illustration and description only and does not limit the scope of the application of the present specification. Various modifications and alterations to the flow may occur to those skilled in the art, given the benefit of this description. However, such modifications and variations are intended to be within the scope of the present description.

Having thus described the basic concepts, it will be apparent to those of ordinary skill in the art having read this application that the foregoing disclosure is to be construed as illustrative only and is not limiting of the application. Various modifications, improvements and adaptations of the present application may occur to those skilled in the art, although they are not explicitly described herein. Such modifications, improvements and adaptations are proposed in the present application and thus fall within the spirit and scope of the exemplary embodiments of the present application.

Also, this application uses specific language to describe embodiments of the application. For example, "one embodiment," "an embodiment," and/or "some embodiments" mean a certain feature, structure, or characteristic described in connection with at least one embodiment of the present application. Therefore, it is emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" or "an alternative embodiment" in various places throughout this specification are not necessarily all referring to the same embodiment. Furthermore, some features, structures, or characteristics of one or more embodiments of the present application may be combined as appropriate.

Similarly, it should be noted that in the preceding description of embodiments of the application, various features are sometimes grouped together in a single embodiment, figure, or description thereof for the purpose of streamlining the disclosure aiding in the understanding of one or more of the embodiments. This method of disclosure, however, is not to be interpreted as reflecting an intention that the claimed subject matter requires more features than are expressly recited in each claim. Rather, the inventive body should possess fewer features than the single embodiment described above.

Claims (10)

1. A blade thermo-engine coupling test section, comprising:

the first cover body is provided with a through hole;

the second cover body is detachably connected with the first cover body so as to form a gas channel with openings at two ends;

one end of the pull rod is used for entering the gas channel through the through hole to be connected with a blade crown of the blade to be tested, the other end of the pull rod is used for being connected with an output end of a tensile machine, and a tenon of the blade to be tested is detachably mounted in a mortise of the second cover body;

the sleeve is arranged at the through hole on the outer side of the first cover body and used for sleeving and sealing the pull rod; and

and the fixed mounting part is arranged on the outer wall surface of the first cover body and/or the second cover body and is used for fixing the position of the first cover body and/or the second cover body.

2. The blade thermo-mechanical coupling test section according to claim 1, wherein the fixed mounting portion is a lifting lug formed by extending the outer wall surface of the first cover body and/or the second cover body outwards or a reinforcing rib provided with a through hole.

3. The blade heat engine coupling test section as claimed in claim 1, wherein the first cover body comprises an upper cover plate and two side wall plates connected with the upper cover plate, the second cover body comprises a lower cover plate, one end of each side wall plate is connected with the upper cover plate, the other end of each side wall plate is detachably connected with the lower cover plate, so that a gas channel is formed jointly, and the fixed mounting part is arranged on the outer wall surfaces of the two side wall plates.

4. The blade thermo-mechanical coupling test section according to claim 3, wherein the connecting surfaces between the side wall plate and the lower cover plate are respectively a concave-convex surface which is embedded with each other.

5. The blade heat engine coupling test section as claimed in claim 1, wherein pneumatic sealing channels are symmetrically arranged at positions on two sides of the sleeve, an air outlet end of each pneumatic sealing channel is communicated with the through hole, the sectional area of a gap between the surface of the pull rod and the through hole is smaller than that of the air outlet end of each pneumatic sealing channel, and the area ratio of the two is 1: s, S is greater than or equal to 10.

6. The blade thermo-mechanical coupling test section according to claim 1, wherein at least one accompanying blade conforming to the shape and structure of the blade to be tested is installed on the inner side of the second cover body in the transverse direction of the gas channel so as to simulate the working environment in which the blade to be tested is actually located.

7. The blade thermo-engine coupling test section according to claim 6, wherein the second cover body is provided with a cold air pipeline which is respectively communicated with the inner cavity of the blade to be tested and the inner cavity of each companion lining blade.

8. The blade thermo-mechanical coupling test section as claimed in claim 7, wherein the end of the pull rod connected with the blade to be tested is provided with a cold air groove, and the cold air groove is communicated with the inner cavity to discharge cold air passing through the inner cavity of the blade to be tested.

9. The vane heat engine coupling test segment of claim 7, wherein a gap is formed between the accompanying vane and the inner wall surface of the first cover body, and the gap is communicated with an inner cavity of the accompanying vane.

10. A vane heat engine coupling test system, comprising:

a blade thermo-mechanical coupling test section according to any one of claims 1 to 9;

the combustion section is connected with the blade thermal engine coupling test section to provide high-temperature fuel gas;

the fuel supply system is connected with the combustion section to supply fuel;

an air supply system connected to the combustion section to provide compressed air; and

and the cooling system is connected with the thermal engine coupling test section of the blade to provide a cooling medium.

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