Turbine blowdown test pressure ratio continuous adjustment device and method

Abstract

The present application relates to turbine blowing test device and method, specifically relates to turbine blowing test pressure ratio continuous adjusting device and method, its purpose is to solve the existing turbine blowing test method cannot continuously adjust pressure ratio, test efficiency is low, test precision is poor, and the problems such as expensive price, adjusting precision is poor, resolution is low of using large-diameter regulating valve;The present application is simultaneously provided with back pressure orifice plate and bypass pipe equipped with regulating valve on turbine outlet pipe, uses regulating valve to adjust turbine pressure ratio, so that the device can continuously test after once calibration;The present application can also be equipped with bypass pipe with high-pressure gas source, pressure reducing valve, pre-pressure temperature measuring instrument of sonic nozzle, sonic nozzle and stop valve on turbine outlet pipe, the turbine pressure ratio is adjusted by adjusting pressure reducing valve, and continuous test can also be realized after once calibration of the device.

Description

Technical Field

[0001] This invention relates to a turbine blowing test apparatus and method, specifically to a turbine blowing test pressure ratio continuous adjustment apparatus and method. Background Technology

[0002] The turbine is the power source of an engine and is known as the "heart" of the engine. Whether it is a turbine in a space engine or a turbine in an aircraft engine, it needs to undergo ground-based wind tests before being installed in the engine to obtain key performance parameters such as turbine efficiency, flow area, axial force, and reaction force.

[0003] One existing turbine blowing test method is as follows:

[0004] First, gas at a specific temperature and pressure is supplied to the turbine inlet. A backpressure orifice plate is installed at the turbine outlet, creating a backpressure environment and establishing a pressure ratio between the turbine inlet and outlet to simulate the engine's operating pressure ratio. Next, the turbine speed is gradually increased while key performance parameters such as turbine efficiency, flow area, axial force, and reaction force are measured. The relationship curves between these key performance parameters and the turbine speed under the current inlet and outlet pressure ratios are then obtained and analyzed. For subsequent tests, a different sized backpressure orifice plate is used at the turbine outlet, and the above process is repeated to obtain the relationship curves between the key performance parameters and the turbine speed under a second turbine inlet and outlet pressure ratio. This process of continuously changing the backpressure orifice plate size continues until tests are completed under all inlet and outlet pressure ratio conditions.

[0005] The drawback of this method is:

[0006] Because the back pressure orifice plate needs to be reinstalled before each test under each operating condition, and to ensure measurement accuracy, the measuring equipment for turbine efficiency and axial force needs to be recalibrated on-site before each test under each operating condition, the test process involves repeatedly performing the operations of "installing the back pressure orifice plate, calibrating the measuring equipment on-site, conducting the air blowing test, and interpreting the data." For several operating conditions, this process needs to be repeated at least several times, resulting in very low test efficiency. At the same time, due to the differences in the processing and assembly of different turbines, the thermal expansion and contraction of the turbine and back pressure orifice plate caused by ambient temperature, the fluctuation of the test gas temperature, and the limited specifications of the back pressure orifice plate, it is impossible to guarantee that the inlet and outlet pressure ratio can be accurately adjusted to the target value, resulting in the inability to continuously adjust the back pressure and poor test accuracy.

[0007] Another existing turbine blowing test method is:

[0008] The turbine outlet back pressure orifice plate in the above-mentioned turbine blowing test method is replaced with a regulating valve with continuously adjustable flow area to achieve continuous adjustment of pressure ratio.

[0009] The drawback of this method is:

[0010] In actual testing, the gas flow rate of the turbine blowing test was above 15 kg / s, and the turbine outlet pressure was very low, about 0.2 MPa. This resulted in the flow coefficient of the regulating valve, i.e., the Cv value, being above 1200, and the diameter being above 300 mm. If flow resistance loss is considered, the actual turbine outlet pipe diameter may need to reach above 500 mm. Using this test method, the actual pressure ratio adjustment process is only within a 10% variation range of the regulating valve opening. This method cannot avoid the problems of high price, poor adjustment accuracy, and low resolution of the large-diameter regulating valve used in this method. Summary of the Invention

[0011] The main purpose of this invention is to solve the problems of existing turbine blowing test methods, such as inability to continuously adjust the pressure ratio, low test efficiency, poor test accuracy, and the high cost, poor adjustment accuracy, and low resolution of the large-diameter regulating valves used. This invention provides a device and method for continuous adjustment of the pressure ratio in turbine blowing tests.

[0012] To achieve the above-mentioned objectives, the present invention provides the following technical solution:

[0013] A turbine blowing test pressure ratio continuous adjustment device includes a turbine inlet pipe, a turbine, a turbine outlet pipe and an exhaust pipe connected in sequence, and a measuring unit;

[0014] The turbine is provided with a turbine inlet and a turbine outlet; the turbine inlet pipe is connected to the turbine inlet, and the turbine outlet pipe is connected to the turbine outlet;

[0015] The measuring unit includes a turbine inlet pressure and temperature measuring instrument, a turbine outlet pressure and temperature measuring instrument, and a turbine parameter measuring device for measuring turbine performance parameters;

[0016] A back pressure orifice plate is provided inside the turbine outlet pipe;

[0017] Its special feature is:

[0018] It also includes a bypass pipe and a regulating valve; one end of the bypass pipe is located between the turbine outlet and the back pressure orifice plate, and the other end is located on the exhaust stack;

[0019] The regulating valve is installed on the bypass pipe, and the flow area of ​​the regulating valve is proportional to the opening degree. It is used to regulate the gas flow rate of the bypass pipe, thereby realizing the regulation of the turbine inlet and outlet pressure ratio.

[0020] Furthermore, the diameter of the turbine outlet pipe is greater than or equal to the diameter of the turbine outlet;

[0021] The diameter of the bypass pipe is larger than the maximum flow area of ​​the regulating valve. The equivalent diameter, of which the maximum flow area We obtain it from the following formula:

[0022] ;

[0023] in, The flow area adjustment margin of the control valve can be arbitrarily selected within the range of 0 to 0.35; , These are the turbine outlet gas pressures. The sum of the flow areas of the back pressure orifice plate and the regulating valve at maximum and minimum values, in meters. 2 ;

[0024] The diameter of the exhaust pipe is larger than the diameter of the turbine outlet pipe.

[0025] Furthermore, a throat for ventilation is machined in the center of the back pressure orifice plate, and the diameter of the throat is... It is obtained through the following formula:

[0026] ;

[0027] ;

[0028] ;

[0029] ;

[0030] ;

[0031] Among them, diameter The unit is m; , Turbine pressure ratio The minimum and maximum values ​​are expressed in Pa. , These are the turbine outlet gas pressures. The maximum and minimum values, in Pa; The flow coefficient of the back pressure orifice plate is 0.6 to 1. The flow rate of gas passing through the turbine is expressed in kg / s. This refers to the gas temperature at the turbine outlet, expressed in Kelvin (K). is the gas constant, with a value of 8.31451 J / (mol·K). The average molecular weight of the gas is expressed in kg / mol. The gas adiabatic index; The pressure measured by the turbine inlet pressure-temperature measuring instrument;

[0032] The turbine outlet gas pressure The temperature was measured using a turbine outlet pressure and temperature measuring instrument.

[0033] Meanwhile, the present invention also provides a method for continuous adjustment of the pressure ratio in a turbine blowing test, which is characterized by including the following steps:

[0034] Step 1: Assemble the turbine blowing test pressure ratio continuous adjustment device described above, and calibrate the turbine parameter measuring equipment; set the turbine pressure ratio test point. , , ... ,and , , ... Complete the pre-experiment preparations; where n≥2;

[0035] Step 2, adjust the opening of the regulating valve. This makes the turbine pressure ratio At the minimum value ;

[0036] Step 3: Gas is introduced into the turbine inlet pipe through the gas generator to drive the turbine to rotate, thereby increasing the pressure measured by the turbine inlet pressure and temperature measuring instrument. and temperature The preset pressure and temperature targets are reached and maintained; the turbine speed is then set to the initial value.

[0037] Step 4: Adjust the turbine parameter measuring device to gradually increase the turbine speed until the preset target speed value is reached; use the turbine parameter measuring device to measure and record the turbine efficiency, axial force, and flow area.

[0038] Step 5: Adjust the turbine parameter measuring equipment to gradually reduce the turbine speed until it returns to the initial value;

[0039] Step 6, according to the turbine pressure ratio test point set in Step 1 , , ... Adjust the opening of the regulating valve sequentially, repeating steps 4 and 5 for measurement after each adjustment, until... At that time, turbine pressure ratio Reaching the maximum value Each adjustment requires adjusting the opening degree of the regulating valve. Adjust to:

[0040] ;

[0041] Step 7: Stop supplying gas into the turbine inlet pipe to complete the turbine blowing test with continuous pressure ratio adjustment.

[0042] Furthermore, in step 2, when the opening degree of the regulating valve is 0, the corresponding turbine pressure ratio is... We obtain it from the following formula:

[0043] ;

[0044] When the opening degree of the regulating valve is 1, the corresponding turbine pressure ratio is... We obtain it from the following formula:

[0045] .

[0046] Meanwhile, the present invention also provides another turbine blowing test pressure ratio continuous adjustment device, including a turbine inlet pipe, a turbine, a turbine outlet pipe and an exhaust pipe connected in sequence, and a measuring unit;

[0047] The turbine is provided with a turbine inlet and a turbine outlet; the turbine inlet pipe is connected to the turbine inlet, and the turbine outlet pipe is connected to the turbine outlet;

[0048] The measuring unit includes a turbine inlet pressure and temperature measuring instrument, a turbine outlet pressure and temperature measuring instrument, and a turbine parameter measuring device for measuring turbine performance parameters;

[0049] A back pressure orifice plate is provided inside the turbine outlet pipe;

[0050] Its special feature is:

[0051] It also includes a bypass pipe; one end of the bypass pipe is located between the turbine outlet and the back pressure orifice plate, and the other end is equipped with a high-pressure air source; along the airflow direction, the bypass pipe is sequentially equipped with a pressure reducing valve, a sonic nozzle inlet pressure and temperature measuring instrument, a sonic nozzle, and a shut-off valve.

[0052] Furthermore, the diameter of the turbine outlet pipe is greater than or equal to the diameter of the turbine outlet;

[0053] The diameter of the exhaust pipe is larger than the diameter of the turbine outlet pipe;

[0054] The pressure reducing valve has a flow regulation margin for the bypass pipe. The scope is:

[0055] ;

[0056] The back pressure orifice plate has a throat machined in the center for ventilation, and the diameter of the throat is... It is obtained through the following formula:

[0057] ;

[0058] ;

[0059] ;

[0060] ;

[0061] in, , They are respectively with , The sum of the gas flow rates through the turbine and the bypass pipe.

[0062] Furthermore, the sonic nozzle operates at supersonic speeds, and the inner diameter of the center of the sonic nozzle... Smaller than the inner diameter at both ends of the sonic nozzle;

[0063] inner diameter We obtain it from the following formula:

[0064] ;

[0065] Among them, inner diameter The unit is m; The value range is 0 to 1; This represents the maximum gas supply flow rate in the bypass pipe, expressed in kg / s. Gas pressure in front of the sonic nozzle The minimum value, in Pa; The temperature of the gas before the sonic nozzle is expressed in Kelvin. The flow coefficient of the sonic nozzle ranges from 0.6 to 1.

[0066] Gas pressure in front of the sonic nozzle The pressure and temperature were measured using a sonic nozzle inlet pressure and temperature measuring instrument.

[0067] Meanwhile, the present invention also provides another method for continuous adjustment of the turbine blowing test pressure ratio, which is characterized by including the following steps:

[0068] Step 1: Assemble the other turbine blowing test pressure ratio continuous adjustment device described above, and calibrate the turbine parameter measuring equipment; set the turbine pressure ratio test point. , , ... ,and , , ... Complete the pre-experiment preparations; where n≥2;

[0069] Step 2: Gas is introduced into the turbine inlet pipe through the gas generator to drive the turbine to rotate, thereby increasing the pressure measured by the turbine inlet pressure and temperature measuring instrument. and temperature The preset pressure and temperature targets are reached and maintained; the turbine speed is then set to the initial value.

[0070] Step 3: Adjust the pressure reducing valve to adjust the gas pressure in front of the sonic nozzle. = Simultaneously, the shut-off valve is opened, thus adjusting the turbine pressure ratio. At maximum value ;

[0071] Step 4: Adjust the turbine parameter measuring device to gradually increase the turbine speed until the preset target speed value is reached; use the turbine parameter measuring device to measure the turbine efficiency, axial force, and flow area.

[0072] Step 5: Adjust the turbine parameter measuring device to gradually reduce the turbine speed until it returns to the initial value;

[0073] Step 6, according to the turbine pressure ratio test point set in Step 1 , , ... Adjust the pressure reducing valves sequentially to regulate the gas pressure in front of the sonic nozzle. The high-pressure gas source discharges gas through the bypass pipe into the turbine outlet pipe. After each adjustment, steps 4-5 are repeated for measurement until the turbine pressure ratio is reached. Reaching the minimum value Each adjustment requires adjusting the gas pressure in front of the sonic nozzle. Adjust to:

[0074] ;

[0075] Step 7: Stop supplying gas into the turbine inlet pipe to complete the turbine blowing test with continuous pressure ratio adjustment.

[0076] Furthermore, in step 3, when the gas pressure in front of the sonic nozzle is at its maximum, the corresponding turbine pressure ratio is... We obtain it from the following formula:

[0077] ;

[0078] When the gas pressure in front of the sonic nozzle is 0, the corresponding turbine pressure ratio is... We obtain it from the following formula:

[0079] .

[0080] Compared with the prior art, the beneficial effects of the present invention are:

[0081] 1. The present invention provides a device and method for continuous adjustment of turbine blowing test pressure ratio, which sets the turbine outlet flow area variation range as an equivalent regulating valve and the constant range as a back pressure orifice plate. The back pressure orifice plate and the regulating valve are used in parallel to achieve continuous adjustment of turbine inlet and outlet pressure ratio. In addition, during the test, the regulating valve can accurately adjust the turbine outlet pressure ratio to the pressure ratio operating point, which effectively improves the test accuracy.

[0082] 2. Another turbine blowing test pressure ratio continuous adjustment device and method provided by the present invention adjusts the turbine outlet pressure by mixing different flow rates of gas in front of the back pressure orifice plate after the turbine outlet, and adjusts the flow rate of the mixed gas by adjusting the pressure in front of the sonic nozzle. It has the advantages of simple operation, the mixed gas flow rate can be continuously changed online, and the adjustment accuracy is high.

[0083] 3. The turbine blowing test pressure ratio continuous adjustment device and method provided by the present invention can meet the test conditions of all pressure ratio operating points with a single calibration before the test, which simplifies the test process and improves the test efficiency. Compared with the method of replacing the back pressure orifice plate, the cycle can be shortened by 60%. At the same time, it avoids the use of traditional large-diameter regulating valves, reduces equipment costs, and improves the pressure ratio adjustment accuracy and resolution. Attached Figure Description

[0084] Figure 1 This is a schematic diagram of the structure of a first embodiment of the turbine blowing test pressure ratio continuous adjustment device of the present invention;

[0085] Figure 2 This is a schematic diagram of the structure of Embodiment 2 of the turbine blowing test pressure ratio continuous adjustment device of the present invention;

[0086] Explanation of reference numerals in the attached figures:

[0087] 1-Turbine outlet pipe; 2-Back pressure orifice plate; 21-Throat; 3-Bypass pipe; 4-Regulating valve; 5-Exhaust stack; 6-Turbine outlet pressure and temperature measuring instrument; 7-Turbine inlet pressure and temperature measuring instrument; 8-Turbine inlet pipe; 9-Turbine; 91-Turbine inlet; 92-Turbine outlet; 10-Turbine parameter measuring equipment; 11-Pressure reducing valve; 12-Pressure and temperature measuring instrument before sonic nozzle; 13-Sonic nozzle; 14-Stop valve; 15-High-pressure air source. Detailed Implementation

[0088] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0089] Example 1

[0090] A turbine blowing test pressure ratio continuous adjustment device, the specific structure of which is as follows: Figure 1As shown, it includes a turbine inlet pipe 8, a turbine 9, a turbine outlet pipe 1 and an exhaust stack 5 connected in sequence, as well as a turbine inlet pressure and temperature measuring instrument 7, a turbine outlet pressure and temperature measuring instrument 6, and a turbine parameter measuring device 10 for measuring the performance parameters of the turbine 9.

[0091] The turbine 9 is provided with a turbine inlet 91 and a turbine outlet 92; the turbine inlet pipe 8 is connected to the turbine inlet 91, and the turbine outlet pipe 1 is connected to the turbine outlet 92. The diameter of the turbine outlet pipe 1 is determined by flow resistance calculation based on the flow rate, pressure and temperature of the gas flowing through it, and is greater than or equal to the diameter of the turbine outlet 92. In this embodiment, the diameter of the turbine outlet pipe 1 is 600 mm, and the diameter of the turbine outlet 92 is 300 mm.

[0092] The diameter of exhaust pipe 5 is larger than the diameter of turbine outlet pipe 1, and is set to 900 mm.

[0093] A back pressure orifice plate 2 is provided inside the turbine outlet pipe 1;

[0094] It also includes a bypass pipe 3 and a regulating valve 4; one end of the bypass pipe 3 is located between the turbine outlet 92 and the back pressure orifice plate 2, and the other end is located on the exhaust pipe 5; the turbine outlet pipe 1 and the bypass pipe 3 flow through the same gas;

[0095] The regulating valve 4 is installed on the bypass pipe 3, and the flow area of ​​the regulating valve 4 is proportional to the opening degree. It is used to regulate the gas flow rate of the bypass pipe 3, thereby realizing the regulation of the turbine inlet and outlet pressure ratio.

[0096] Specifically, the diameter of the bypass pipe 3 is determined by flow resistance calculation based on the gas flow rate, pressure, and temperature, and is greater than the maximum flow area of ​​the regulating valve 4. The equivalent diameter, of which the maximum flow area We obtain it from the following formula:

[0097] ;

[0098] in, In this embodiment, to adjust the flow area of ​​regulating valve 4, the adjustment margin is... The value is 0.15; , These are the turbine outlet gas pressures. The sum of the flow areas of the back pressure orifice plate 2 and the regulating valve 4 at maximum and minimum values, in meters. 2 The calculation results are 0.028764 and 0.031212;

[0099] In this embodiment, =0.0035m 2The selected specifications for regulating valve 4 are DN150PN1.6MPa; the selected specifications for bypass pipe 3 are ϕ168✕3, with a pressure resistance of 4MPa.

[0100] A throat 21 is machined in the center of the back pressure orifice plate 2, and the diameter of the throat 21 is... It is obtained through the following formula:

[0101] ;

[0102] ;

[0103] ;

[0104] ;

[0105] ;

[0106] Among them, diameter The unit is meters (m). , Turbine pressure ratio The minimum and maximum values ​​are expressed in Pa. , These are the turbine outlet gas pressures. The maximum and minimum values, in Pa, are calculated to be 255000 and 235000 respectively. The flow coefficient of the back pressure orifice plate 2 is 0.9; The gas flow rate through turbine 1 is expressed in kg / s and is set to 17.5. The gas temperature at turbine outlet 92°C is expressed in Kelvin (K) and is 288°C. is the gas constant, with a value of 8.31451 J / (mol·K). The average molecular weight of the gas is expressed in kg / mol and is 0.028964. The gas adiabatic index is 1.41. The pressure measured by turbine inlet pressure and temperature measuring instrument 7; turbine outlet gas pressure. The temperature was measured by turbine outlet pressure and temperature measuring instrument 6;

[0107] During the regulation process of regulating valve 4, the flow area is directly proportional to the opening degree; the opening degree of regulating valve 4 is from... Adjust to (1- During the process, the flow area of ​​regulating valve 4 changes from... Increase to (1- ) The sum of the flow areas of the corresponding back pressure orifice plate 2 and regulating valve 3 is from Increase to The corresponding turbine outlet gas pressure from Reduce to The corresponding turbine pressure ratio is from = / Increase to = / .

[0108] In this embodiment, during the adjustment of the opening of regulating valve 4 from 15% to 85%, the flow area changes from 0.000525m². 2 Increased to 0.002975m 2 The sum of the flow areas of the corresponding back pressure orifice plate 2 and regulating valve 3 is 0.028764m². 2 Increased to 0.031212m 2 The corresponding turbine outlet gas pressure When the pressure is reduced from 255,000 Pa to 235,000 Pa, the corresponding turbine pressure ratio increases from 2.353 to 2.553.

[0109] This embodiment also provides a method for continuous adjustment of the turbine blowing test pressure ratio, including the following steps:

[0110] Step 1: Assemble the turbine blowing test pressure ratio continuous adjustment device described above, and calibrate the turbine parameter measuring device 10; set the turbine pressure ratio test point. , , ,and , , Complete the preparations before the experiment;

[0111] Step 2, adjust the opening of regulating valve 4. =15%, making the turbine pressure ratio At the minimum value ,at this time = =2.353;

[0112] Step 3: Gas is introduced into the turbine inlet pipe 8 through the gas generator, driving the turbine 9 to rotate, thereby increasing the pressure measured by the turbine inlet pressure and temperature measuring instrument 7. and temperature The preset pressure target value of 0.6MPa and temperature target value of 345K are reached and remain unchanged; at this time, the speed of turbine 9 is 6000rpm, which is set as the initial value;

[0113] Step 4: Adjust the turbine parameter measuring device 10 to gradually increase the turbine 9 speed until it reaches the preset target speed value of 10,000 rpm; use the turbine parameter measuring device 10 to measure and record the turbine 9 efficiency, axial force, and flow area.

[0114] Step 5: Adjust the turbine parameter measuring device 10 to gradually reduce the turbine 9 speed until it returns to the initial value of 6000 rpm;

[0115] Step 6, according to the turbine pressure ratio test point set in Step 1 , , Adjust the opening of regulating valve 4 sequentially, repeating steps 4-5 for measurement after each adjustment; until... At that time, turbine pressure ratio Reaching the maximum value Each adjustment requires adjusting the opening of regulating valve 4. Adjust to:

[0116] ,

[0117] ;

[0118] Step 7: Stop supplying gas into the turbine inlet pipe 8 to complete the turbine blowing test with continuous pressure ratio adjustment.

[0119] During the above adjustment process, when the opening of the regulating valve 4 is 0, the corresponding turbine pressure ratio is... We obtain it from the following formula:

[0120] ;

[0121] When the opening degree of regulating valve 4 is 1, its corresponding turbine pressure ratio is... We obtain it from the following formula:

[0122] .

[0123] Example 2

[0124] A turbine blowing test pressure ratio continuous adjustment device, the specific structure of which is as follows: Figure 2 As shown, it includes a turbine inlet pipe 8, a turbine 9, a turbine outlet pipe 1 and an exhaust stack 5 connected in sequence, as well as a turbine inlet pressure and temperature measuring instrument 7, a turbine outlet pressure and temperature measuring instrument 6, and a turbine parameter measuring device 10 for measuring the performance parameters of the turbine 9.

[0125] The turbine 9 is provided with a turbine inlet 91 and a turbine outlet 92; the turbine inlet pipe 8 is connected to the turbine inlet 91, and the turbine outlet pipe 1 is connected to the turbine outlet 92. The diameter of the turbine outlet pipe 1 is determined by flow resistance calculation based on the flow rate, pressure and temperature of the gas flowing through it, and is greater than or equal to the diameter of the turbine outlet 92. In this embodiment, the diameter of the turbine outlet pipe 1 is 600 mm, and the diameter of the turbine outlet 92 is 300 mm.

[0126] The diameter of exhaust pipe 5 is larger than the diameter of turbine outlet pipe 1, and is set to 900 mm.

[0127] A back pressure orifice plate 2 is provided inside the turbine outlet pipe 1;

[0128] It also includes a bypass pipe 3; one end of the bypass pipe 3 is located between the turbine outlet 92 and the back pressure orifice plate 2, and the other end is provided with a high-pressure gas source 15; a pressure reducing valve 11, a sonic nozzle inlet pressure and temperature measuring instrument 12, a sonic nozzle 13 and a shut-off valve 14 are arranged sequentially on the bypass pipe 3 along the airflow direction; the turbine outlet pipe 1 and the bypass pipe 3 are through the same gas;

[0129] With the maximum supply flow and highest operating pressure (flow rate) of bypass pipe 3 =2.138kg / s, pressure =6.85MPa) Select pressure reducing valve 11 and shut-off valve 14. The pressure reducing valve 11 is selected with specification DN50Cv12, inlet PN35MPa (the maximum pressure of high pressure gas source 15 is 35MPa), and maximum outlet working pressure 10MPa; the shut-off valve 14 is selected with specification DN50PN10MPa.

[0130] The diameter of bypass pipe 3 is based on the maximum flow rate of the gas passing through it. Pressure and temperature are determined through flow resistance calculations. The bypass pipe 3 after pressure reducing valve 11 is selected with a specification of ϕ60. 3. Pressure resistant 10MPa, the bypass pipe 3 before the pressure reducing valve 11 is selected with a specification of ϕ42. 6. Withstands pressure of 35MPa;

[0131] The flow regulation margin of pressure reducing valve 11 to bypass pipe 3 The scope is:

[0132] ;

[0133] In this embodiment, The value is 0.146; a throat 21 for ventilation is machined in the center of the back pressure orifice plate 2, and the diameter of the throat 21 is... It is obtained through the following formula:

[0134] ;

[0135] ;

[0136] ;

[0137] ;

[0138] Among them, diameter =212mm, =2.138kg / s; , These are the lowest and highest turbine pressure ratios, respectively, in Pa. , These are the turbine outlet gas pressures. The maximum and minimum values, in Pa, are calculated to be 255000 and 235000 respectively. , They are respectively with , The sum of the gas flow rates through turbine 9 and bypass pipe 3, in kg / s, is calculated to be 17.8122 and 19.3281, respectively. The flow coefficient of the back pressure orifice plate 2 is 0.9; The gas flow rate through turbine 9 is expressed in kg / s and is valued at 17.5. The gas temperature at turbine outlet 92 is expressed in Kelvin and is 288. The gas temperature in bypass pipe 3 is the same as that in turbine outlet pipe 1, and mixing of the two does not cause a temperature change. is the gas constant, with a value of 8.31451 J / (mol·K). The average molecular weight of the gas is expressed in kg / mol and is 0.028964. The gas adiabatic index is 1.41; the turbine outlet gas pressure. The temperature was measured by turbine outlet pressure and temperature measuring instrument 6;

[0139] The sonic nozzle 13 operates in a sonic state, and the inner diameter of the middle part of the sonic nozzle 13 is... The inner diameter at both ends of the sonic nozzle 13 is less than the inner diameter. We obtain it from the following formula:

[0140] ;

[0141] in, This represents the maximum gas supply flow rate in bypass pipe 3, expressed in kg / s. Gas pressure in front of sonic nozzle 13 The minimum value, in Pa, is determined by the principle that it must be at least... More than 3 times, in this embodiment the value is taken as 1. 10 6 ; The gas temperature before the sonic nozzle 13 is in Kelvin and has a value of 295. The flow coefficient of the sonic nozzle 13 is 0.95; the gas pressure before the sonic nozzle 13 is... The temperature was measured by the pressure and temperature measuring instrument 12 before the sonic nozzle.

[0142] Adjusting the pressure reducing valve 11 increases the gas pressure in front of the sonic nozzle. from =1 10 6 Pa rises to =5.85 10 6 Pa, corresponding to the bypass pipe 3 flow rate from =0.3122kg / s increased to =1.8281 kg / s, corresponding to the sum of the gas flow rates through turbine 9 and bypass passage 3 from =17.8122kg / s increased to =19.3821 kg / s, corresponding to the turbine outlet gas pressure from =0.235 10 6 Pa rises to =0.255 10 6 Pa, corresponding to the turbine pressure ratio from = / =2.553 decreased to = / =2.353;

[0143] This embodiment also provides a method for continuous adjustment of the turbine blowing test pressure ratio, including the following steps:

[0144] Step 1: Assemble the turbine blowing test pressure ratio continuous adjustment device described above, and calibrate the turbine parameter measuring device 10; set the turbine pressure ratio test point. , , ,and , , Complete the preparations before the experiment;

[0145] Step 2: Gas is introduced into the turbine inlet pipe 8 through the gas generator, driving the turbine 9 to rotate, so that the pressure measured by the turbine inlet pressure and temperature measuring instrument 7 is... and temperature The preset pressure target value of 0.6MPa and temperature target value of 345K are reached and remain unchanged; at this time, the speed of turbine 9 is 4000rpm, which is set as the initial value;

[0146] Step 3: Adjust the pressure reducing valve 11 to adjust the gas pressure in front of the sonic nozzle 13. = =1 10 6 Pa; simultaneously open shut-off valve 14 to increase turbine pressure ratio =2.553;

[0147] Step 4: Adjust the turbine parameter measuring device 10 to gradually increase the turbine 9 speed until it reaches the preset target speed value of 10,000 rpm; use the turbine parameter measuring device 10 to measure the turbine 9 efficiency, axial force, and flow area.

[0148] Step 5: Adjust the turbine parameter measuring device 10 to gradually reduce the turbine 9 speed until it returns to the initial value of 4000 rpm;

[0149] Step 6, according to the turbine pressure ratio test point set in Step 1 , , Adjust the pressure reducing valve 11 sequentially to regulate the gas pressure in front of the sonic nozzle 13. , The high-pressure gas source 15 discharges gas through the bypass pipe 3 into the turbine outlet pipe 1. After each adjustment, steps 4-5 are repeated for measurement; until the turbine pressure ratio is reached. Reaching the minimum value Each adjustment requires adjusting the gas pressure in front of the sonic nozzle 13. Adjust to:

[0150] ,

[0151] ;

[0152] Step 7: Stop supplying gas into the turbine inlet pipe 8 to complete the turbine blowing test with continuous pressure ratio adjustment.

[0153] During the above adjustment process, when the gas pressure in front of the sonic nozzle 13 is at its maximum, the corresponding turbine pressure ratio is... We obtain it from the following formula:

[0154] ;

[0155] When the gas pressure in front of the sonic nozzle 13 is 0, the corresponding turbine pressure ratio is We obtain it from the following formula:

[0156] .

[0157] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit them. For those skilled in the art, modifications can be made to the specific technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. However, these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions protected by the present invention.

Claims

1. A turbine blowing test pressure ratio continuous adjustment device, comprising a turbine inlet pipe (8), a turbine (9), a turbine outlet pipe (1) and an exhaust pipe (5) connected in sequence, and a measuring unit; The turbine (9) is provided with a turbine inlet (91) and a turbine outlet (92); the turbine inlet pipe (8) is connected to the turbine inlet (91), and the turbine outlet pipe (1) is connected to the turbine outlet (92); The measuring unit includes a turbine inlet pressure and temperature measuring instrument (7), a turbine outlet pressure and temperature measuring instrument (6), and a turbine parameter measuring device (10) for measuring the performance parameters of the turbine (9). The turbine outlet pipe (1) is provided with a back pressure orifice plate (2); Its features are: It also includes a bypass pipe (3) and a regulating valve (4); one end of the bypass pipe (3) is located between the turbine outlet (92) and the back pressure orifice plate (2), and the other end is located on the exhaust pipe (5); The regulating valve (4) is installed on the bypass pipe (3), and the flow area of ​​the regulating valve (4) is proportional to the opening degree. It is used to regulate the gas flow rate of the bypass pipe (3), thereby realizing the regulation of the turbine inlet and outlet pressure ratio.

2. The turbine blowing test pressure ratio continuous adjustment device according to claim 1, characterized in that: The diameter of the turbine outlet pipe (1) is greater than or equal to the diameter of the turbine outlet (92); The diameter of the bypass pipe (3) is larger than the maximum flow area of ​​the regulating valve (4). The equivalent diameter, of which the maximum flow area We obtain it from the following formula: ； in, To provide the flow area adjustment margin for regulating valve (4), , These are the turbine outlet gas pressures. The sum of the flow areas of the back pressure orifice plate (2) and the regulating valve (4) at the maximum and minimum values; The diameter of the exhaust pipe (5) is larger than the diameter of the turbine outlet pipe (1).

3. The turbine blowing test pressure ratio continuous adjustment device according to claim 1, characterized in that: The back pressure plate (2) has a throat (21) machined in the center, and the diameter of the throat (21) is... It is obtained through the following formula: ； ； ； ； ； in, , Turbine pressure ratio The minimum and maximum values; , These are the turbine outlet gas pressures. The maximum and minimum values; The flow coefficient of the back pressure orifice plate (2); The gas flow rate passing through the turbine (9); The gas temperature at the turbine outlet (92); is the gas constant, with a value of 8.31451 J / (mol·K). The average molecular weight of the gas; The gas adiabatic index; The pressure measured by the turbine inlet pressure and temperature measuring instrument (7); The turbine outlet gas pressure The temperature was measured by a turbine outlet pressure and temperature measuring instrument (6).

4. A method for continuously adjusting the pressure ratio in a turbine blowing test, characterized in that, Includes the following steps: Step 1: Assemble the turbine blowing test pressure ratio continuous adjustment device according to any one of claims 1-3, and calibrate the turbine parameter measuring device (10); set the turbine pressure ratio test point. , , ... ,and , , ... Complete the pre-experiment preparations; where n≥2; Step 2, adjust the opening of the regulating valve (4). This makes the turbine pressure ratio At the minimum value ; Step 3: Gas is introduced into the turbine inlet pipe (8) through the gas generator to drive the turbine (9) to rotate, so that the pressure measured by the turbine inlet pressure and temperature measuring instrument (7) is... and temperature The preset pressure and temperature target values ​​are reached and remain unchanged; the rotational speed of the turbine (9) is set to the initial value at this time; Step 4: Adjust the turbine parameter measuring device (10) to gradually increase the turbine (9) speed until the preset speed target value is reached; use the turbine parameter measuring device (10) to measure and record the turbine (9) efficiency, axial force, and flow area; Step 5: Adjust the turbine parameter measuring device (10) to gradually reduce the turbine (9) speed until it returns to the initial value; Step 6, according to the turbine pressure ratio test point set in Step 1 , , ... Adjust the opening of the regulating valve (4) sequentially, and repeat steps 4-5 for measurement after each adjustment until... At that time, turbine pressure ratio Reaching the maximum value Each adjustment requires adjusting the opening degree of the regulating valve (4). Adjust to: ； Step 7: Stop supplying gas into the turbine inlet pipe (8) to complete the turbine blowing test with continuous pressure ratio adjustment.

5. The method for continuous adjustment of turbine blowing test pressure ratio according to claim 4, characterized in that: In step 2, when the opening degree of the regulating valve (4) is 0, the corresponding turbine pressure ratio is... We obtain it from the following formula: ； When the opening degree of the regulating valve (4) is 1, the corresponding turbine pressure ratio is We obtain it from the following formula: 。 6. A turbine blowing test pressure ratio continuous adjustment device, comprising a turbine inlet pipe (8), a turbine (9), a turbine outlet pipe (1) and an exhaust pipe (5) connected in sequence, and a measuring unit; The turbine (9) is provided with a turbine inlet (91) and a turbine outlet (92); the turbine inlet pipe (8) is connected to the turbine inlet (91), and the turbine outlet pipe (1) is connected to the turbine outlet (92); The measuring unit includes a turbine inlet pressure and temperature measuring instrument (7), a turbine outlet pressure and temperature measuring instrument (6), and a turbine parameter measuring device (10) for measuring the performance parameters of the turbine (9). The turbine outlet pipe (1) is provided with a back pressure orifice plate (2); Its features are: It also includes a bypass pipe (3); one end of the bypass pipe (3) is located between the turbine outlet (92) and the back pressure orifice plate (2), and the other end is provided with a high-pressure gas source (15); a pressure reducing valve (11), a sonic nozzle front pressure and temperature measuring instrument (12), a sonic nozzle (13) and a shut-off valve (14) are arranged sequentially on the bypass pipe (3) along the airflow direction.

7. The turbine blowing test pressure ratio continuous adjustment device according to claim 6, characterized in that: The diameter of the turbine outlet pipe (1) is greater than or equal to the diameter of the turbine outlet (92); The diameter of the exhaust pipe (5) is larger than the diameter of the turbine outlet pipe (1); The pressure reducing valve (11) provides a flow regulation margin for the bypass pipe (3). The scope is: ； The back pressure orifice plate (2) has a throat (21) machined in the center for ventilation, and the diameter of the throat (21) is... It is obtained through the following formula: ； ； ； ； in, , They are respectively with , The sum of the gas flow rates through the turbine (9) and the bypass pipe (3).

8. The turbine blowing test pressure ratio continuous adjustment device according to claim 7, characterized in that: The sonic nozzle (13) operates in a sonic state, and the inner diameter of the middle part of the sonic nozzle (13) Smaller than the inner diameter at both ends of the sonic nozzle (13); inner diameter We obtain it from the following formula: ； in, The maximum gas supply flow rate in the bypass pipe (3); Gas pressure in front of the sonic nozzle (13) The minimum value; The gas temperature before the sonic nozzle (13); The flow coefficient of the sonic nozzle (13); The gas pressure in front of the sonic nozzle (13) The pressure and temperature were measured by a sonic nozzle inlet pressure and temperature measuring instrument (12).

9. A method for continuously adjusting the pressure ratio in a turbine blowing test, characterized in that, Includes the following steps: Step 1: Assemble the turbine blowing test pressure ratio continuous adjustment device according to any one of claims 6-8, and calibrate the turbine parameter measuring device (10); set the turbine pressure ratio test point. , , ... ,and , , ... Complete the pre-experiment preparations; where n≥2; Step 2: Gas is introduced into the turbine inlet pipe (8) through the gas generator to drive the turbine (9) to rotate, so that the pressure measured by the turbine inlet pressure and temperature measuring instrument (7) is... and temperature The preset pressure and temperature target values ​​are reached and remain unchanged; the rotational speed of the turbine (9) is set to the initial value at this time; Step 3, adjust the pressure reducing valve (11) to adjust the gas pressure in front of the sonic nozzle (13) so that the pressure is adjusted accordingly. = Simultaneously, the shut-off valve (14) is opened, thereby increasing the turbine pressure ratio. At maximum value ; Step 4: Adjust the turbine parameter measuring device (10) to gradually increase the turbine (9) speed until the preset speed target value is reached; use the turbine parameter measuring device (10) to measure the turbine (9) efficiency, axial force and flow area; Step 5: Adjust the turbine parameter measuring device (10) to gradually reduce the turbine (9) speed until it returns to the initial value; Step 6, according to the turbine pressure ratio test point set in Step 1 , , ... Adjust the pressure reducing valve (11) in sequence to adjust the gas pressure in front of the sonic nozzle (13). The high-pressure gas source (15) discharges the gas into the turbine outlet pipe (1) through the bypass pipe (3). After each adjustment, steps 4-5 are repeated for measurement until the turbine pressure ratio is reached. Reaching the minimum value Each adjustment requires adjusting the gas pressure in front of the sonic nozzle (13). Adjust to: ； Step 7: Stop supplying gas into the turbine inlet pipe (8) to complete the turbine blowing test with continuous pressure ratio adjustment.

10. The method for continuous adjustment of turbine blowing test pressure ratio according to claim 9, characterized in that: In step 3, when the gas pressure in front of the sonic nozzle (13) is at its maximum, the corresponding turbine pressure ratio is... We obtain it from the following formula: ； When the gas pressure in front of the sonic nozzle (13) is 0, the corresponding turbine pressure ratio is We obtain it from the following formula: 。

Images