CN112345193B - Wind tunnel test measuring system for aerodynamic performance of counter-rotating propeller fan of open rotor engine - Google Patents
Wind tunnel test measuring system for aerodynamic performance of counter-rotating propeller fan of open rotor engine Download PDFInfo
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- CN112345193B CN112345193B CN202011185152.5A CN202011185152A CN112345193B CN 112345193 B CN112345193 B CN 112345193B CN 202011185152 A CN202011185152 A CN 202011185152A CN 112345193 B CN112345193 B CN 112345193B
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention discloses a wind tunnel test measurement system for aerodynamic performance of a counter-rotating propeller fan of an open rotor engine, which aims to solve the technical problems of simulation of working conditions of the counter-rotating propeller fan of the engine and respective simultaneous measurement of the aerodynamic performance of the propeller fan under the wind tunnel scale test condition. The test system comprises: the device comprises a supporting device, a first paddle fan force measuring device, a second paddle fan force measuring device, a shell, a connecting flange, a water cooling sleeve, an attack angle mechanism, a wind tunnel, a control system and a measuring system. During testing, the wind tunnel provides a uniform flow field, the control system controls the attack angle mechanism, the first paddle fan force measuring device and the second paddle fan force measuring device to realize expected model attitude and rotation speed simulation, and the measuring system respectively measures and obtains aerodynamic forces of the first paddle fan and the second paddle fan. The device is simple and reliable, and is convenient to install and operate; the test requirements of different incoming flow Mach numbers, the inflow angle of the paddle disk, the rotating speed of the paddle disk and the combined form of the blade pitch can be met; two rotary shaft balances are adopted to realize accurate measurement of the pneumatic performance of the double-propeller fan respectively.
Description
Technical Field
The invention relates to a wind tunnel test system, in particular to a wind tunnel test measurement system for the aerodynamic performance of a counter-rotating propeller fan of an open rotor engine, and belongs to the technical field of test aerodynamic measurement.
Background
With the further increase in the demands for low fuel consumption, emissions, etc. of aircraft engines and the emergence of more stringent airworthiness regulations, the use of open rotor engines in commercial aircraft and military transport aircraft has been reconsidered. The thrust of the open rotor engine, also called as a non-ducted fan engine or a contra-rotating propeller engine, is generated by a double-row contra-rotating propeller fan comprising a plurality of wide-chord thin-blade type sweepback blades, has the characteristics of low oil consumption of the turboprop engine and suitability for high-speed flight of the turboprop engine, has an effective ducted ratio as high as 25-60, and can keep higher propulsion efficiency (the propulsion efficiency can be improved by about 20-30 percent compared with the traditional turboprop engine). In recent years, with the application of high performance/low noise paddle fan design and transmission design technologies, the noise/vibration problem of open rotor engines has been gradually solved, and is considered as an attractive alternative power for the new generation of commercial aircraft and military transport vehicles to achieve low carbon targets.
In the development process of the open rotor engine, in order to improve the performance of the open rotor engine to the maximum extent, the aerodynamic characteristics of the counter-rotating propeller fan need to be accurately obtained through a ground wind tunnel test. At present, the classical measurement method is to directly install a powered engine scaling model on a wind tunnel external strain balance, and obtain the total force difference on the model by measuring the force of the engine in working and non-working states, so as to obtain the estimated value of the aerodynamic performance of the paddle fan. However, this method does not distinguish the mutual interference between the fan and the supporting structure, hub, body; meanwhile, the friction damping of the driving system cannot be deducted, and the real propelling efficiency of the engine cannot be obtained; in addition, due to the integrated measurement, the aerodynamic performance of a single paddle fan and the aerodynamic interference characteristics between double paddle fans cannot be obtained.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the invention overcomes the defects of the prior art, provides a wind tunnel test measuring system for the pneumatic performance of the rotor fan of the open rotor engine aiming at the problem of the wind tunnel test precision measurement of the pneumatic performance of the rotor fan of the open rotor engine, adopts a double-rotating-shaft balance force measurement technology, solves the technical problems of engine working condition simulation, respective simultaneous measurement of the pneumatic performance of the rotor fan and the like under the wind tunnel scale test condition, and realizes the accurate acquisition of the pneumatic performance and the propulsion efficiency of the rotor fan of the open rotor engine.
The technical solution of the invention is as follows: an open rotor engine is to test measurement system of rotor blade aerodynamic performance wind tunnel includes: the device comprises a supporting device, a first paddle fan force measuring device, a second paddle fan force measuring device, a shell, an attack angle mechanism, a wind tunnel, a control system and a measuring system;
the supporting device supports the first paddle fan force measuring device and the second paddle fan force measuring device, the supporting device is installed on the attack angle mechanism, and the attack angle mechanism is installed in the wind tunnel; the supporting device, the first paddle fan force measuring device and the second paddle fan force measuring device are packaged through the shell to form a streamline model, and a bracket of the supporting device, the first paddle fan and the second paddle fan extend out of the surface of the shell; the first paddle fan force measuring device is used for rotation simulation and aerodynamic force measurement of the first paddle fan; the second paddle fan force measuring device is used for rotation simulation and aerodynamic measurement of the second paddle fan;
the wind tunnel provides a uniform flow field, the control system controls the attack angle mechanism, the first paddle fan force measuring device and the second paddle fan force measuring device to realize model attitude and rotating speed simulation, and the measuring system respectively measures and obtains aerodynamic forces of the first paddle fan and the second paddle fan.
The supporting device comprises a supporting rod, a joint and a bracket; one end of the supporting rod is arranged in the joint and limited by a flange plate on the supporting rod, and the end part of the supporting rod is fixed by a fastener; the joint is arranged on the bracket, the bracket supports the supporting rod, and the bracket is arranged on the attack angle mechanism; the support is of a symmetrical thick-wing structure, and the support rod and the support are both provided with wiring holes.
The first propeller fan force measuring device comprises a first driving motor, a first driving shaft, a first rotating shaft balance, a first propeller hub, a first propeller fan, a first remote measuring device and a first signal receiving device; the supporting rod sequentially penetrates into the first driving motor and the first driving shaft along central shafts of the first driving motor and the first driving shaft, the fixed end of the first driving motor is arranged on a flange plate of the supporting rod, and one end of the first driving shaft is arranged on the rotating end of the first driving motor; the first rotary shaft balance is arranged at the other end of the first driving shaft, positioned through a spline and fixed through a fastener; the first propeller fans are installed on the first propeller hub and are installed on the first rotating shaft balance together; the first telemetering device is arranged on an inner ring of the first rotary shaft balance, and the first signal receiving device is arranged on the supporting rod and is adjacent to the first telemetering device.
The wind tunnel test measurement system for the aerodynamic performance of the contra-rotating propeller fan of the open rotor engine further comprises a connecting flange, wherein the second propeller fan force measurement device comprises a second driving motor, a second driving shaft, a second rotating shaft balance, a second propeller hub, a second propeller fan, a second remote measurement device and a second signal receiving device; the first driving shaft penetrates into the second driving motor along the central shaft of the second driving motor, and the fixed end of the second driving motor is installed on the fixed end of the first driving motor through a connecting flange; the second driving shaft is sleeved on the first driving shaft, one end of the second driving shaft is installed on the rotating end of the second driving motor, and one end of the first driving shaft, which is provided with the first rotating shaft balance, extends out of the other end of the second driving shaft; the second rotary shaft balance is arranged at the other end of the second driving shaft, positioned through a spline and fixed through a fastener; the second propeller fan is arranged on the second propeller hub and is jointly arranged on the second rotary shaft balance, the second telemetering device is arranged on an inner ring of the second rotary shaft balance, and the second signal receiving device is arranged on the fixed end of the second driving motor and is adjacent to the second telemetering device; the first driving motor and the second driving motor are also sleeved with water cooling sleeves, the side walls of the water cooling sleeves are hollow shells, and water inlet holes and water outlet holes are formed in the end faces of the water cooling sleeves.
The first driving shaft and the second driving shaft are both of hollow structures and are nested and assembled with the supporting rod, the supporting rod penetrates through the first driving shaft in a non-contact manner, and the first driving shaft penetrates through the second driving shaft in a non-contact manner; the unilateral clearance between branch and the first drive shaft, between first drive shaft and the second drive shaft is 1 ~ 2 mm.
The first telemetering device comprises a power supply module, a data acquisition module, a wireless transmission module and a first rotating speed photoelectric tube; the first telemetering device acquires signals of the first rotary shaft balance through the data acquisition module, and sends the signals to the first signal receiving device through the wireless transmission module after amplification, A/D conversion and filtering; the first rotating speed photoelectric tube receives the infrared light sent by the first signal receiving device;
the second telemetering device comprises a power supply module, a data acquisition module, a wireless transmission module and a second rotating speed photoelectric tube; the second telemetering device acquires signals of the second rotary shaft balance through the data acquisition module, and the signals are amplified, subjected to A/D conversion and filtered and then sent to the second signal receiving device through the wireless transmission module; and the second rotating speed photoelectric tube receives the infrared light sent by the second signal receiving device.
The first signal receiving device comprises a wireless receiving module and a first infrared light source; the first signal receiving device receives a signal of the first rotary shaft balance sent by the first telemetering device through the wireless receiving module; the first infrared light source provides continuous infrared light;
the second signal receiving device comprises a wireless receiving module and a second infrared light source; the second signal receiving device receives a signal of the second rotary shaft balance sent by the second telemetering device through the wireless receiving module; the second infrared light source provides continuous infrared light.
The first rotating shaft balance and the second rotating shaft balance respectively comprise an inner ring, an outer ring and spoke type measuring beams, four groups of spoke type measuring beams are uniformly distributed between the inner ring and the outer ring along the circumferential direction, and each group of spoke type measuring beams comprises three column beams; the outer surface of outer loop evenly sets up a plurality of splines along circumference, the internal surface of inner ring evenly sets up a plurality of spline grooves along circumference.
The first paddle fan also comprises a first jackscrew and a first angle block, wherein one end of the first angle block is a plane, and the other end of the first angle block is an inclined plane with an angle; a groove is formed in the cylindrical section of the end part of the first propeller fan and is connected with the cylindrical surface of the first propeller hub in a matched mode; when the first propeller fan is installed, the cylindrical section of the first propeller fan is inserted into the first propeller hub, the first angle block is installed from the side face of the first propeller hub, the inclined plane of the first angle block is matched with the groove surface on the cylindrical section of the first propeller fan, the first angle block is tightly pressed by the first jackscrew, the first propeller fan is connected with the first propeller hub, and the propeller pitch is determined; the second fan is connected to the second hub in the same manner.
The shell comprises a first shell, a second shell, a third shell and a fourth shell; one end of the second shell is arranged on the flange of the support rod; the first shell is arranged at the head of the second shell, the third shell is arranged at the tail end of the support rod, and the fourth shell is arranged at the tail end of the third shell; labyrinth structures are respectively formed between the second shell and the second hub, between the second hub and the first hub and between the first hub and the third shell, so that contact between the parts is avoided, and external airflow can be prevented from entering the inner cavity of the model.
Compared with the prior art, the invention has the beneficial effects that:
the invention provides a wind tunnel test system for the aerodynamic performance of a contra-rotating propeller fan, which aims at the problem of insufficient wind tunnel measurement capability of the aerodynamic performance of the contra-rotating propeller fan of the existing open rotor engine and can realize accurate acquisition of the aerodynamic performance and the propulsion efficiency of the propeller fan. The method comprises the following specific steps:
(1) the wind tunnel test measurement system for the aerodynamic performance of the rotor fan of the open rotor engine effectively solves the problems of real simulation of the working condition of the rotor fan of the engine and direct acquisition of the aerodynamic performance of the rotor fan under the wind tunnel scale test condition.
(2) The wind tunnel test measurement system for the aerodynamic performance of the contra-rotating propeller fan of the open rotor engine provided by the invention adopts two rotary shaft balances to accurately measure the aerodynamic performance of the double propeller fans respectively, and can realize the differentiation of the aerodynamic interference of the propeller fans, the support/the propeller hub, the deduction of the friction damping of a driving system and the acquisition of the aerodynamic interference characteristic between the double propeller fans.
(3) The wind tunnel test measurement system for the aerodynamic performance of the contra-rotating propeller fan of the open rotor engine can realize the simulation of different incoming flow Mach numbers, the inflow angle of the propeller disc, the rotating speed of the propeller disc and the combination form of the propeller pitch, and can meet the requirements of related test capabilities.
(4) The wind tunnel test measuring system for the aerodynamic performance of the contra-rotating propeller fan of the open rotor engine provided by the invention has the advantages of simple and reliable device, low processing cost and convenience in installation and operation; the replacement of the propeller pitch of the double-propeller fan can be realized on the premise of not dismantling the driving and measuring device, the test cost is low, and the efficiency is high.
Drawings
FIG. 1 is a wind tunnel test measurement system for aerodynamic performance of a counter-rotating propeller fan of an open rotor engine according to the present invention;
FIG. 2 is a schematic view of the assembly of the supporting device, the first/second paddle fan force measuring device and the housing of the present invention;
FIG. 3 is a schematic view of the support device of the present invention;
FIG. 4 is a schematic view of a first paddle fan force measuring device of the present invention;
FIG. 5 is a schematic view of a second paddle fan force measuring device of the present invention;
FIG. 6 is a schematic view of a rotary shaft balance according to the present invention;
FIG. 7 is a schematic diagram of the water jacket structure of the present invention;
FIG. 8 is a schematic view of a fan-hub installation method of the present invention;
FIG. 9 is a schematic view of the labyrinth structure of the present invention;
Detailed Description
The following describes the embodiments of the present invention in detail with reference to fig. 1 to 9.
The invention discloses a wind tunnel test measurement system, which aims to solve the technical problems of the simulation of the working condition of a contra-rotating double-propeller fan of an open rotor engine, the measurement of the pneumatic performance of the propeller fan and the like under the wind tunnel scale test condition and realize the accurate acquisition of the pneumatic performance and the propulsion efficiency of the contra-rotating propeller fan. Specifically, the wind tunnel test measurement system for the aerodynamic performance of the counter-rotating propeller fan of the open rotor engine is provided, as shown in fig. 1 to fig. 2, and comprises a supporting device, a first propeller fan force measuring device, a second propeller fan force measuring device, a shell, a connecting flange 20, a water cooling jacket 21, an attack angle mechanism 24, a wind tunnel 25, a control system 26 and a measurement system 27.
Referring to fig. 2 and 3, the supporting device includes a bar 1, a joint 2, and a bracket 22. The supporting rod 1 is of a cylindrical structure comprising a flange plate, is installed on the joint 2 and is tightened and fixed by a nut, the joint 2 is installed on the support 22, and the supporting device, the angle of attack mechanism 24 and the joint form a supporting device for supporting the first paddle fan force measuring device, the second paddle fan force measuring device and the shell. The support 22 is a symmetrical thick wing structure, and the support rod 1 and the support 22 are both provided with wiring holes for arrangement of driving/measuring electric circuits and water-cooling pipes.
Referring to fig. 2 and 4, the first fan force measuring device includes a first driving motor 4, a first driving shaft 5, a first rotation shaft balance 16, a first hub 10, a first fan 11, a first telemetry device 15, and a first signal receiving device 14. The first driving motor 4 is of a hollow structure, the fixed end of the first driving motor is installed on a flange plate of the supporting rod 1, the first driving shaft 5 is installed at the rotating end of the first driving motor 4, the first rotary shaft balance 16 is installed on the first driving shaft 5 and is positioned through a spline and fixed with a nut in a tensioning mode, the first fan 11 is installed on the first hub 10 and is installed on the first rotary shaft balance 16 together, the first telemetering device 15 is installed on an inner ring of the first rotary shaft balance 16, and the first signal receiving device 14 is installed on the supporting rod 1 and is adjacent to the first telemetering device 15. The first paddle fan force measuring device is formed by the paddle fan force measuring device and is used for rotation simulation and aerodynamic force measurement of the first paddle fan.
In this embodiment, preferably, the first driving shaft 5 is a hollow structure, the supporting rod 1 can pass through the first driving shaft 5 without contact, and the one-sided gap between the two is 1-2 mm.
In this embodiment, preferably, referring to fig. 6, the first rotary-shaft balance 16 is of an annular "spoke" structure, and the "spoke" measuring beam is of a three-column beam form and is divided into four groups uniformly distributed between the inner ring and the outer ring of the balance. The balance outer ring is provided with a spline for rotational positioning between the hub and the balance; the balance inner ring is provided with a spline groove for rotationally positioning the driving shaft and the balance.
In this embodiment, referring to fig. 4, the first telemetry device 15 is a dedicated circuit board, and includes a power module, an acquisition module, an amplification module, an a/D conversion module, a filter, and a wireless transmission module, and the first signal receiving device 14 includes a wireless receiving module, which together form a balance signal acquisition and transmission device, and can acquire and transmit a rotating balance signal to the non-rotating fixed end. In addition, the first telemetering device 15 further comprises a rotating speed photoelectric cell 1501, and the first signal receiving device 14 further comprises an infrared light source 1401, which together form a rotating speed sensor for measuring the rotating speed and the rotating position of the rotary shaft balance. The first telemetering device 15 acquires signals of the first rotary shaft balance 16 through the data acquisition module, and sends the signals to the first signal receiving device 14 through the wireless transmission module after amplification, A/D conversion and filtering; the first rotating speed photocell 1501 receives the infrared light sent by the first signal receiving device 14; the first signal receiving device 14 receives the signal of the first rotary shaft balance 16 sent by the first telemetering device 15 through a wireless receiving module; the first infrared light source 1401 continuously emits infrared rays.
With reference to fig. 2 and 5, the second fan force measuring device includes a second driving motor 6, a second driving shaft 7, a second rotation shaft balance 17, a second hub 9, a second fan 8, a second telemetering device 18, and a second signal receiving device 19. The second driving motor 6 is a hollow structure, the fixed end of the second driving motor is installed on the fixed end of the first driving motor 4 through a connecting flange 20, the second driving shaft 7 is installed on the rotating end of the second driving motor 6, the second rotary shaft balance 17 is installed on the second driving shaft 7 and is positioned through splines and tightened and fixed through nuts, the second paddle fan 8 is installed on the second paddle hub 9 and is installed on the second rotary shaft balance 17 together, the second remote measuring device 18 is installed on the inner ring of the second rotary shaft balance 17, and the second signal receiving device 19 is installed on the fixed end of the second driving motor 6 and is adjacent to the second remote measuring device 18. The two paddle fans form a second paddle fan force measuring device together, and the second paddle fan force measuring device is used for rotation simulation and aerodynamic force measurement of the second paddle fan.
In this embodiment, preferably, the second driving shaft 7 is a hollow structure, the first driving shaft 5 can pass through the second driving shaft 7 without contact, and the single-side gap between the two is 1-2 mm.
In this embodiment, the second rotary axis balance 17 has the same structure as the first rotary axis balance 16.
In this embodiment, the second telemetry unit 18 is of the same composition and function as the first telemetry unit 15; the second signal receiving means 19 has the same composition and function as the first signal receiving means 14.
In this embodiment, preferably, with reference to fig. 7, the first driving motor 4 and the second driving motor 6 are further provided with a water cooling jacket 21, the water cooling jacket 21 is a cylindrical hollow shell structure, and the end surface is provided with a water inlet hole and a water outlet hole. During the test, cooling water gets into through the inlet opening to discharge by the apopore, form the circulation, be used for driving motor heat dissipation.
In the present embodiment, the housing includes a first housing 23, a second housing 3, a third housing 12, and a fourth housing 13, which are all thin shell structures. The second shell 3 is arranged on a flange of the support rod 1, the first shell 23 is arranged on the second shell 3, the third shell 12 is arranged at the tail end of the support rod 1, and the fourth shell 13 is arranged on the third shell 12, so that an engine outer surface is formed, and installation spaces are provided for the first paddle fan force measuring device and the second paddle fan force measuring device.
In this embodiment, preferably, referring to fig. 9, three labyrinth structures are formed between the second casing 3 and the second hub 9, between the second hub 9 and the first hub 10, and between the first hub 10 and the third casing 12, respectively, so that the first hub 10 and the second hub 9 can rotate independently while no contact is ensured between the respective parts, and the external airflow can be prevented from entering the inner cavity of the mold, and the distance between the labyrinth structures is 1mm to 1.5 mm.
In this embodiment, referring to fig. 8, the first fan 11 further includes a first jackscrew 1101 and a first angle block 1102, one end of the first angle block 1102 is a plane, the other end is an inclined plane with an angle, a half groove is formed on a cylindrical section of the first fan 11, and the cylindrical section is in cylindrical fit connection with the first hub 10. When the propeller is installed, the cylindrical section of the first propeller fan 11 is inserted into the first propeller hub 10, the first angle block 1102 is installed from the side surface of the first propeller hub 10, the inclined surface of the first angle block is matched with the groove surface of the cylindrical section of the first propeller fan 11, the first angle block is tightly pressed by the first jackscrew 1101, and fastening connection can be achieved; the pitch angle of the paddle fan can be changed by changing the angle blocks with different angles and adopting the same fastening mode.
In this embodiment, the second fan 8 is connected to the second hub and the pitch angle is changed in the same manner as described above.
The assembly sequence of the test apparatus of this embodiment is: a first driving motor 4 and a first driving shaft 5 are arranged on the support rod 1; assembling a second paddle fan force measuring device and installing the second paddle fan force measuring device on the fixed end of the first driving motor 4 through a connecting flange 20; assembling other parts of the first paddle fan force measuring device and installing the other parts on the first driving shaft 5; installing a water cooling cover; mounting the second shell 3 on the support rod 1; the devices are arranged on the joint 2 and the bracket 22 and are arranged on the wind tunnel attack angle mechanism; and assembling other shells to form the whole double-paddle-fan force measuring device. During a wind tunnel test, the wind tunnel 25 provides a uniform flow field, the control system 26 controls the attack angle mechanism 24, the first paddle fan force measuring device and the second paddle fan force measuring device to realize the simulation of the expected model attitude and the rotation speed, and the measurement system 27 respectively measures and obtains the aerodynamic force of the first paddle fan and the aerodynamic force of the second paddle fan.
Those skilled in the art will appreciate that the invention may be practiced without these specific details. The above embodiments are exemplary, and the present invention can be extended to any specific and any novel combination disclosed in the present specification within the scope referred to in the claims, which also fall within the technical scope of the present invention.
The invention has not been described in detail in part of the common general knowledge of those skilled in the art.
Claims (10)
1. The utility model provides an open rotor engine is to experimental measurement system of rotor blade aerodynamic performance wind-tunnel which characterized in that includes: the device comprises a supporting device, a first paddle fan force measuring device, a second paddle fan force measuring device, a shell, an attack angle mechanism (24), a wind tunnel (25), a control system (26) and a measuring system (27);
the supporting device supports the first paddle fan force measuring device and the second paddle fan force measuring device, the supporting device is installed on the attack angle mechanism (24), and the attack angle mechanism (24) is installed in the wind tunnel (25); the supporting device, the first paddle fan force measuring device and the second paddle fan force measuring device are packaged through the shell to form a streamline model, and a bracket (22) of the supporting device, the first paddle fan (11) and the second paddle fan (8) extend out of the surface of the shell; the first paddle fan force measuring device is used for rotation simulation and aerodynamic measurement of the first paddle fan (11); the second paddle fan force measuring device is used for rotation simulation and aerodynamic measurement of the second paddle fan (8);
the wind tunnel (25) provides a uniform flow field, the attack angle mechanism (24), the first paddle fan force measuring device and the second paddle fan force measuring device are controlled through the control system (26) to achieve model attitude and rotation simulation, and the measurement system (27) is used for respectively measuring and obtaining aerodynamic force of the first paddle fan (11) and the second paddle fan (8).
2. The wind tunnel test measurement system for aerodynamic performance of a counter-rotating propeller fan of an open rotor engine according to claim 1, characterized in that the supporting device comprises a support rod (1), a joint (2) and a bracket (22); one end of the support rod (1) is arranged in the joint (2) and limited by a flange plate on the support rod (1), and the end part is fixed by a fastener; the joint (2) is arranged on a support (22), the support (22) supports the supporting rod (1), and the support (22) is arranged on an attack angle mechanism (24); the support (22) is of a symmetrical thick wing type structure, and the support rod (1) and the support (22) are both provided with wiring holes.
3. The wind tunnel test measurement system for aerodynamic performance of a contra-rotating propeller fan of an open rotor engine according to claim 2, characterized in that the first propeller fan force measurement device comprises a first driving motor (4), a first driving shaft (5), a first rotating shaft balance (16), a first propeller hub (10), a first propeller fan (11), a first remote measurement device (15) and a first signal receiving device (14); the supporting rod (1) sequentially penetrates through the first driving motor (4) and the first driving shaft (5) along the central shafts of the first driving motor (4) and the first driving shaft (5), the fixed end of the first driving motor (4) is installed on a flange of the supporting rod (1), and one end of the first driving shaft (5) is installed on the rotating end of the first driving motor (4); the first rotary shaft balance (16) is arranged at the other end of the first driving shaft (5), positioned through a spline and fixed through a fastener; the first propeller fans (11) are mounted on a first propeller hub (10) and are jointly mounted on a first rotary shaft balance (16); the first telemetering device (15) is arranged on an inner ring of the first rotary shaft balance (16), and the first signal receiving device (14) is arranged on the strut (1) and is adjacent to the first telemetering device (15).
4. The wind tunnel test measurement system for aerodynamic performance of a contra-rotating propeller fan of an open rotor engine according to claim 3, characterized by further comprising a connecting flange (20), wherein the second propeller fan force measurement device comprises a second driving motor (6), a second driving shaft (7), a second rotating shaft balance (17), a second propeller hub (9), a second propeller fan (8), a second remote measurement device (18) and a second signal receiving device (19); the first driving shaft (5) penetrates into the second driving motor (6) along the central shaft of the second driving motor (6), and the fixed end of the second driving motor (6) is installed on the fixed end of the first driving motor (4) through a connecting flange (20); the second driving shaft (7) is sleeved on the first driving shaft (5), one end of the second driving shaft (7) is installed at the rotating end of the second driving motor (6), and one end of the first driving shaft (5), which is provided with the first rotating shaft balance (16), extends out of the other end of the second driving shaft (7); the second rotating shaft balance (17) is arranged at the other end of the second driving shaft (7), is positioned through a spline and is fixed through a fastener; the second fan (8) is arranged on a second hub (9) and is jointly arranged on a second rotating shaft balance (17), the second telemetering device (18) is arranged on an inner ring of the second rotating shaft balance (17), and the second signal receiving device (19) is arranged on a fixed end of the second driving motor (6) and is adjacent to the second telemetering device (18); the water cooling jacket (21) is sleeved on the first driving motor (4) and the second driving motor (6), the side wall of the water cooling jacket (21) is a hollow shell, and a water inlet hole and a water outlet hole are formed in the end face of the water cooling jacket.
5. The wind tunnel test measurement system for aerodynamic performance of a counter-rotating propeller fan of an open rotor engine according to claim 4, characterized in that the first driving shaft (5) and the second driving shaft (7) are both of a hollow structure and are nested and assembled with the strut (1), the strut (1) penetrates through the first driving shaft (5) in a non-contact manner, and the first driving shaft (5) penetrates through the second driving shaft (7) in a non-contact manner; the unilateral clearance between the support rod (1) and the first driving shaft (5) and between the first driving shaft (5) and the second driving shaft (7) is 1-2 mm.
6. The wind tunnel test measurement system for aerodynamic performance of a counter-rotating propeller fan of an open rotor engine according to claim 5, characterized in that the first telemetering device (15) comprises a first power supply module, a first data acquisition module, a first wireless transmission module and a first rotating speed photoelectric tube (1501); the first remote measuring device (15) collects signals of the first rotary shaft balance (16) through the first data acquisition module, and the signals are amplified, A/D converted and filtered and then sent to the first signal receiving device (14) through the first wireless transmission module; the first rotating speed photoelectric tube (1501) receives infrared light sent by the first signal receiving device (14);
the second telemetering device (18) comprises a second power supply module, a second data acquisition module, a second wireless transmission module and a second rotating speed photoelectric tube (1801); the second telemetering device (18) acquires signals of the second rotary shaft balance (17) through a second data acquisition module, and sends the signals to a second signal receiving device (19) through a second wireless transmission module after amplification, A/D conversion and filtering; the second rotating speed photocell (1801) receives the infrared light sent by the second signal receiving device (19).
7. The wind tunnel test measurement system for aerodynamic performance of a counter-rotating propeller fan of an open rotor engine according to claim 6, characterized in that the first signal receiving device (14) comprises a first wireless receiving module and a first infrared light source (1401); the first signal receiving device (14) receives a signal of a first rotating shaft balance (16) sent by the first telemetering device (15) through a first wireless receiving module; a first infrared light source (1401) providing continuous infrared light;
the second signal receiving device (19) comprises a second wireless receiving module and a second infrared light source (1901); the second signal receiving device (19) receives the signal of the second rotary shaft balance (17) transmitted by the second telemetering device (18) through a second wireless receiving module; the second infrared light source (1901) provides continuous infrared light.
8. The wind tunnel test measurement system for the aerodynamic performance of the counter-rotating propeller fan of the open rotor engine according to claim 7, wherein the first rotating shaft balance (16) and the second rotating shaft balance (17) respectively comprise an inner ring, an outer ring and four sets of spoke-type measurement beams, the four sets of spoke-type measurement beams are uniformly distributed between the inner ring and the outer ring along the circumferential direction, and each set of spoke-type measurement beams comprises three column beams; the outer surface of outer loop evenly sets up a plurality of splines along circumference, the internal surface of inner ring evenly sets up a plurality of spline grooves along circumference.
9. The wind tunnel test measurement system for aerodynamic performance of a counter-rotating propeller fan of an open rotor engine according to claim 8, characterized in that the first propeller fan (11) further comprises a first jackscrew (1101) and a first angle block (1102), one end of the first angle block (1102) is a plane, and the other end of the first angle block is an inclined plane with an angle; a groove is formed in the cylindrical section of the end part of the first propeller fan (11) and is connected with the cylindrical surface of the first propeller hub (10) in a matched mode; when the propeller is installed, the cylindrical section of the first propeller fan (11) is inserted into the first propeller hub (10), the first angle block (1102) is installed from the side face of the first propeller hub (10), the inclined face of the first angle block is matched with the groove face on the cylindrical section of the first propeller fan (11), the first angle block is tightly pressed by the first jackscrew (1101), connection between the first propeller fan (11) and the first propeller hub (10) is achieved, and the propeller pitch is determined; the second fan (8) is connected to the second hub (9) in the same way.
10. The wind tunnel test measurement system for aerodynamic performance of a counter-rotating propeller fan of an open rotor engine according to claim 9, characterized in that the housing comprises a first housing (23), a second housing (3), a third housing (12) and a fourth housing (13); one end of the second shell (3) is arranged on the flange of the support rod (1); the first shell (23) is arranged at the head of the second shell (3), the third shell (12) is arranged at the tail end of the support rod (1), and the fourth shell (13) is arranged at the tail end of the third shell (12); labyrinth structures are formed between the second shell (3) and the second hub (9), between the second hub (9) and the first hub (10), and between the first hub (10) and the third shell (12).
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| CN113267320B (en) * | 2021-07-19 | 2021-09-28 | 中国空气动力研究与发展中心超高速空气动力研究所 | Water cooling device for rod type balance of high-temperature wind tunnel |
| CN114563155B (en) * | 2022-03-14 | 2023-05-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Open rotor pneumatic performance evaluation test device |
| US20230322412A1 (en) * | 2022-04-07 | 2023-10-12 | General Electric Company | System and method for testing aircraft engines |
| CN117073958B (en) * | 2023-10-17 | 2023-12-08 | 中国航空工业集团公司沈阳空气动力研究所 | Open rotor engine rotor and stator blade high-speed wind tunnel test device |
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| DE102011013517B4 (en) * | 2011-03-10 | 2012-10-11 | Airbus Operations Gmbh | Propeller system with two contra-rotating propellers, method for detecting the thrust of a propeller system with two contra-rotating propellers and wind tunnel with a propeller system arranged therein model |
| CN107228720B (en) * | 2017-03-31 | 2019-06-04 | 长光卫星技术有限公司 | Duct coaxial double-rotary wing unmanned plane aerodynamic characteristics tests platform |
| CN109357879B (en) * | 2018-10-10 | 2020-07-31 | 中国航发湖南动力机械研究所 | Counter-rotating propeller fan testing device and system |
| CN109186922A (en) * | 2018-11-16 | 2019-01-11 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of wind tunnel test methods of helicopter co-axis double propeller hub model |
| CN110844113B (en) * | 2019-10-12 | 2022-06-03 | 中国直升机设计研究所 | Rigid coaxial dual-rotor test bed capable of simultaneously measuring upper rotor load and lower rotor load |
| CN110803299B (en) * | 2019-10-21 | 2022-09-06 | 中国直升机设计研究所 | Rotary balance for testing rotor load |
| CN111189608B (en) * | 2020-02-26 | 2020-11-27 | 重庆大学 | Counter-rotating propeller test device |
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