Automatic machine matching method for marine supercharger
阅读说明：本技术 一种船用增压器自动配机方法 (Automatic machine matching method for marine supercharger ) 是由 李新宇 王肖路 侯春峰 王政川 谢小华 李鑫 宋剑 于 2021-09-13 设计创作，主要内容包括：本发明公开了一种船用增压器自动配机方法,可以自动完成配机,省时省力。S1、获取配机前参数数据,输入自动配机系统；S2、通过传感器采集设备实际参数数据,输入自动配机系统；S3、对压气机扩压器、涡轮喷嘴环进行标定,将压气机扩压器、涡轮喷嘴环分为多个档位；S4、计算出所需要的标准容积流量、总压比、压气机效率、涡轮当量面积、涡轮效率、增压器总效率,得到压气机规格和涡轮规格；S5、调节压气机开度和涡轮开度,然后将扩压器和喷嘴环设置到此开度所对应的规格档位,进行配机,并计算,与期望得到的结果相对比,如不符合要求,则调节扩压器和喷嘴环的开度,再进行试验,直到达到符合要求的结果。(The invention discloses an automatic machine matching method for a marine supercharger, which can automatically complete machine matching and is time-saving and labor-saving. S1, acquiring parameter data before machine allocation, and inputting the parameter data into an automatic machine allocation system; s2, acquiring actual parameter data of the equipment through a sensor, and inputting the data into an automatic machine matching system; s3, calibrating the compressor diffuser and the turbine nozzle ring, and dividing the compressor diffuser and the turbine nozzle ring into a plurality of gears; s4, calculating the required standard volume flow, total pressure ratio, compressor efficiency, turbine equivalent area, turbine efficiency and total supercharger efficiency to obtain the specification of the compressor and the specification of the turbine; s5, adjusting the opening of the compressor and the opening of the turbine, setting the diffuser and the nozzle ring to the specification gear corresponding to the opening, matching the compressor, calculating, comparing with the expected result, if the result is not satisfactory, adjusting the opening of the diffuser and the nozzle ring, and then testing until the result is satisfactory.)
1. An automatic machine matching method for a marine supercharger is characterized by comprising the following steps:
s1, acquiring parameter data before machine matching: diesel engine cylinder diameter D, diesel engine stroke S, compression ratio epsilon, oil injection starting angle and environment pressure PoAmbient temperature t0Relative humidity, optimum power NeSpeed n of diesel engine, boost pressure PSAir flow rate m of the unitVATemperature t of scavenging airsMaximum gas pressure PVTCylinder exhaust temperature Δ t, turbine outletBack pressure P4Inputting the parameter data into an automatic machine-matching system, wherein the fuel consumption rate be and the fuel low-heat value Hu are used as fuel;
s2, acquiring actual parameter data of the equipment through a sensor: turbine inlet pressure HT1Turbine inlet temperature tK1SInlet temperature T of compressork1sInlet pressure H of compressorK1(ii) a Turbine outlet pressure HT2Turbine outlet temperature tK2SCompressor outlet temperature Tk2sCompressor outlet pressure HK2(ii) a Flow reading V0(ii) a The actual rotating speed, power, oil consumption, flow and explosion pressure of the diesel engine are input into an automatic engine allocation system by a sensor;
s3, the compressor and the turbine have opening adjusting functions, the compressor and the turbine are variable, the compressor diffuser and the turbine nozzle ring are calibrated, the compressor diffuser and the turbine nozzle ring are divided into a plurality of gears, and each gear corresponds to different openings;
s4, preliminarily calculating the required standard volume flow, total pressure ratio, compressor efficiency, turbine equivalent area, turbine efficiency and total supercharger efficiency through diesel engine parameters, and obtaining the specification of the compressor and the specification of the turbine through program comparison;
calculating the area of the turbine:
geometric equivalent area of turbine:
thermodynamic equivalent area machine calculated value: frest＝FT/αT
In the formula, FNNozzle outlet area, FB: the geometric area of the movable blade, wherein alpha T is a flow coefficient;
the geometric equivalent area of the turbine is multiplied by the flow coefficient alphaTValue of (D) as the turbine equivalent area SDThen, the corresponding area of the nozzle ring under the area is found;
s5, adjusting the opening degree of the compressor and the opening degree of the turbine, setting the diffuser and the nozzle ring to a gear corresponding to the opening degree, matching the machine, calculating the data acquired in the step S2 in an automatic matching system, comparing the data with the expected result, adjusting the opening degrees of the diffuser and the nozzle ring if the data do not meet the requirement, and then testing until the result meets the requirement, wherein the calculation process of the automatic matching system is as follows:
the calculation process of the air compressor comprises the following steps:
static pressure at an inlet of the gas compressor:
static pressure at the outlet of the compressor:
mass flow of air:
compressor inlet density: rhoK1＝P1×105×(287.14×(TK1S+273.15))
Compressor inlet speed: c1＝G/(FK1×10-3×ρK1)
Total inlet temperature of the compressor:
static temperature of an inlet of the gas compressor:
total pressure at an inlet of the compressor: pK1＝P1×(TK1/T1)3.5
Compressor outlet density: rhoK2＝P2×105×(287.14×(TK2S+273.15))
Compressor exit speed: c2＝G/(FK2×10-3×ρK2)
Total temperature of an outlet of the gas compressor:
static temperature of an outlet of the gas compressor:
total pressure at the outlet of the compressor: pK2＝P2×(TK2/T2)3.5
Total pressure ratio: II typeK＝PK2/PK1
Compressor efficiency: etaK＝(ΠK-1)×(T0+273.15)/(TK2-(T0+273.15)) turbine calculation process:
turbine inlet static pressure:
turbine gas density: rhoT1＝PT1×10-5/(286.5×(tK1s+273.15))
Turbine gas velocity: cT1＝1.02×G/(FT1×10-3×ρT1)
Turbine inlet static temperature:
total temperature of turbine inlet:
turbine inlet total pressure: pT＝PT1×(tT1/t1)3.778
Turbine outlet static pressure:
turbo expansion ratio: II typeT＝PT/PT2
Turbine adiabatic expansion work: wT＝1082×tT1×(1-1/ΠT)0.26
Adiabatic compression work of compressor:
total supercharger efficiency: etaTC＝WT/WG×0.98。
2. The automatic machine matching method of the marine supercharger according to claim 1, characterized in that: the diffuser and the nozzle ring are both adjusted in opening degree through the electric push rod, and the compressor diffuser and the turbine nozzle ring are divided into a plurality of gears through limiting and calibrating the electric push rod.
3. The automatic machine matching method for the marine supercharger according to claim 2, characterized in that: the compressor diffuser is divided into five stages from HF01 to HF05, and the turbine nozzle ring is divided into ten stages from EF01 to EF 10.
4. The automatic machine matching method of the marine supercharger according to claim 1, characterized in that: the flow coefficient α T is found from a turbine performance graph.
Technical Field
The invention relates to the technical field of turbochargers, in particular to an automatic machine matching method for a marine supercharger.
Background
The turbocharger and the diesel engine are two machines with different working principles and have obviously different working characteristics, and the combined operation of the two machines has a problem of matching and adjusting. The main requirements for matching are: the air supercharging ratio and the flow rate provided by the turbine supercharger in each working cycle of the diesel engine can meet the air intake requirement of the diesel engine; the exhaust of the diesel engine can drive the pressure end of the supercharger; the air inlet characteristic curve of the diesel engine is matched with the operation characteristic curve of the air compressor. The booster of same model is under the unchangeable condition of casing and impeller diameter, changes a small amount of cocurrent component, like nozzle ring, diffuser etc. just can satisfy the requirement of matcing the diesel engine, and present machine flow of joining in marriage generally needs to take several sets of nozzle rings to joining in marriage the quick-witted on-the-spot change of machine, wastes time and energy, very big extravagant manpower and materials.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides an automatic machine matching method for a marine supercharger, which can automatically complete machine matching and is time-saving and labor-saving.
The purpose of the invention is realized as follows:
an automatic machine matching method for a marine supercharger comprises the following steps:
s1, acquiring parameter data before machine matching: diesel engine cylinder diameter D, diesel engine stroke S, compression ratio epsilon, oil injection starting angle and environment pressure PoAmbient temperature t0Relative humidity, optimum power NeSpeed n of diesel engine, boost pressure PSAir flow rate m of the unitVATemperature t of scavenging airsMaximum gas pressure PVTCylinder exhaust temperature Δ t, turbine outlet back pressure P4Inputting the parameter data into an automatic machine-matching system, wherein the fuel consumption rate be and the fuel low-heat value Hu are used as fuel;
s2, acquiring actual parameter data of the equipment through a sensor: turbine inlet pressure HT1Turbine inlet temperature tK1SInlet temperature T of compressork1sInlet pressure H of compressorK1(ii) a Turbine outlet pressure HT2Turbine outlet temperature tK2SCompressor outlet temperature Tk2sCompressor outlet pressure HK2(ii) a Flow reading V0(ii) a The actual rotating speed, power, oil consumption, flow and explosion pressure of the diesel engine are input into an automatic engine allocation system by a sensor;
s3, the compressor and the turbine have opening adjusting functions, the compressor and the turbine are variable, the compressor diffuser and the turbine nozzle ring are calibrated, the compressor diffuser and the turbine nozzle ring are divided into a plurality of gears, and each gear corresponds to different openings;
s4, preliminarily calculating the required standard volume flow, total pressure ratio, compressor efficiency, turbine equivalent area, turbine efficiency and total supercharger efficiency through diesel engine parameters, and obtaining the specification of the compressor and the specification of the turbine through program comparison.
Calculating the area of the turbine:
geometric equivalent area of turbine:
thermodynamic equivalent area machine calculated value: frest＝FT/αT
In the formula, FNNozzle outlet area, FB: the geometric area of the movable blade, wherein alpha T is a flow coefficient;
the geometric equivalent area of the turbine is multiplied by the flow coefficient alphaTValue of (D) as the turbine equivalent area SDThen, the corresponding area of the nozzle ring under the area is checked.
S5, adjusting the opening degree of the compressor and the opening degree of the turbine by the variable diffuser and the variable nozzle ring, setting the diffuser and the nozzle ring to the specification gear corresponding to the opening degree, matching the machine, calculating the data acquired in the step S2 in the automatic matching system, comparing the data with the expected result, if the data do not meet the requirement, adjusting the opening degrees of the diffuser and the nozzle ring, and then testing until the result meets the requirement, wherein the calculation process of the automatic matching system is as follows:
the calculation process of the air compressor comprises the following steps:
static pressure at an inlet of the gas compressor:
static pressure at the outlet of the compressor:
mass flow of air:
compressor inlet density: rhoK1＝P1×105×(287.14×(TK1S+273.15))
Compressor inlet speed: c1＝G/(FK1×10-3×ρK1)
Total inlet temperature of the compressor:
static temperature of an inlet of the gas compressor:
total pressure at an inlet of the compressor: pK1＝P1×(TK1/T1)3.5
Compressor outlet density: rhoK2＝P2×105×(287.14×(TK2S+273.15))
Compressor exit speed: c2＝G/(FK2×10-3×ρK2)
Total temperature of an outlet of the gas compressor:
static temperature of an outlet of the gas compressor:
total pressure at the outlet of the compressor: pK2＝P2×(TK2/T2)3.5
Total pressure ratio: II typeK＝PK2/PK1
Compressor efficiency: etaK＝(∏K-1)×(T0+273.15)/(TK2-(T0+273.15))
The turbine calculation process comprises the following steps:
turbine inlet static pressure:
turbine gas density: rhoT1＝PT1×10-5/(286.5×(tK1S+273.15))
Turbine gas velocity: cT1＝1.02×G/(FT1×10-3×ρT1)
Turbine inlet static temperature:
total temperature of turbine inlet:
turbine inlet total pressure: pT＝PT1×(tT1/t1)3.778
Turbine outlet static pressure:
turbo expansion ratio: II typeT＝PT/PT2
Turbine adiabatic expansion work: wT＝1082×tT1×(1-1/ΠT)0.26
Adiabatic compression work of compressor:
total supercharger efficiency: etaTC＝WT/WG×0.98。
Preferably, the diffuser and the nozzle ring of the gas compressor are divided into a plurality of gears by adjusting the opening degree of the electric push rod and limiting and calibrating the electric push rod.
Preferably, the compressor diffuser is divided into five stages from HF01 to HF05, and the turbine nozzle ring is divided into ten stages from EF01 to EF 10.
Preferably, the flow coefficient α T is found from a turbine performance graph.
By adopting the technical scheme, the automatic matching machine for the supercharger can automatically acquire the data of the supercharger and the diesel engine, analyze and process the test data and realize the automatic matching of the supercharger by controlling the opening and closing areas of the variable nozzle ring and the variable diffuser.
Drawings
FIG. 1 is a schematic flow diagram of the present invention;
FIG. 2 is a schematic diagram of a compressor performance curve;
FIG. 3 is a graph showing the comparison of the calculated results with experimental data.
Detailed Description
An automatic matching method for a marine supercharger (supercharger and diesel engine matching) comprises the following steps:
1. data required before machine allocation: name of diesel engine, cylinder diameter (D), stroke (S), compression ratio (epsilon), start angle of oil injection, and ambient pressure (P)o) Ambient temperature (t)0) Relative humidity, optimum power (N)e) Diesel engine speed (n), boost pressure (P)S) Air flow rate (m) aloneVA) Temperature (t) of scavenging airs) Maximum gas pressure (P)VT) Cylinder exhaust temperature (Δ t), turbine outlet back pressure (P)4) The fuel consumption rate (be) and the fuel low heat value (Hu) are input into the automatic machine-matching system.
2. Data acquisition by sensors: turbine inlet pressure (H)T1) Turbine inlet temperature (t)K1S) Inlet of compressorTemperature (T)k1s) Compressor inlet pressure (H)K1) (ii) a Turbine outlet pressure (H)T2) Turbine outlet temperature (t)K2S) Compressor outlet temperature (T)k2s) Compressor outlet pressure (H)K2) (ii) a Flow reading (V)0) (ii) a Actual speed, power, oil consumption, flow and explosion pressure of the diesel engine. And the data processing unit is acquired through the sensor and displayed.
3. The compressor and the turbine firstly select a specification through diesel engine parameters, wherein the diffuser and the nozzle ring can be adjusted through the electric push rod, so that the adjustment of the diffuser and the nozzle ring is convenient to match the performance of the diesel engine during subsequent automatic machine allocation.
The push rod is firstly subjected to limit calibration, the compressor diffuser is divided into five gears HF01-HF05, the nozzle ring is divided into ten gears EF01-10, and the gears correspond to different flow areas (opening degrees) of each type of diffuser and the nozzle ring.
4. The required standard volume flow, total pressure ratio, compressor efficiency, turbine equivalent area, turbine efficiency and total supercharger efficiency are obtained preliminarily through diesel engine parameters, and the specification of the compressor and the specification of the turbine are obtained through program comparison.
Calculating the area of the turbine:
FNnozzle exit area FB: geometric area of moving blade
Frest＝FT/αT… … … … … … … … thermodynamic equivalent area (computer-aided area)
αTFlow coefficient found (from turbine performance curve plot)
The area calculated by the machine is thermodynamic equivalent area, and is different from geometric equivalent area, and should be multiplied by flow coefficient alphaTThe calculated geometric equivalent area of the turbine is multiplied by the flow coefficient alphaTThe value of (D) is taken as the outlet area S of the nozzle ringD(in the general case, SDAnd calculatedThermodynamic equivalent area has small difference, can be directly substituted for calculation, also can be repeatedly substituted for calculation), then the alpha under said area can be searchedTLet the current SD×αT。
5. The variable diffuser and the variable nozzle ring are used for adjusting the air inlet area and the turbine inlet area of the compressor and then connecting the diffuser and the nozzle ring. Setting a gear corresponding to the flow area, allocating the machine, calculating the data acquired in the step 2 in a program, comparing the calculated data with an expected result, if the calculated data do not meet the requirement, replacing the flow areas of the diffuser and the nozzle ring, and then testing until the result meets the requirement. The software calculation process is as follows:
the calculation process of the air compressor comprises the following steps:
static pressure at an inlet of the gas compressor:
static pressure at the outlet of the compressor:
mass flow of air:
compressor inlet density: rhoK1＝P1×105×(287.14×(TK1S+273.15))
Compressor inlet speed: c1＝G/(FK1×10-3×ρK1)
Total inlet temperature of the compressor:
static temperature of an inlet of the gas compressor:
total pressure at an inlet of the compressor: pK1＝P1×(TK1/T1)3.5
Compressor outlet density: rhoK2＝P2×105×(287.14×(TK2S+273.15))
Compressor exit speed: c2＝G/(FK2×10-3×ρK2)
Total temperature of an outlet of the gas compressor:
static temperature of an outlet of the gas compressor:
total pressure at the outlet of the compressor: pK2＝P2×(TK2/T2)3.5
Total pressure ratio: n shapeK＝PK2/PK1
Compressor efficiency: etaK＝(∏K-1)×(T0+273.15)/(TK2-(T0+273.15)) turbine calculation process:
turbine inlet static pressure:
turbine gas density: rhoT1＝PT1×10-5/(286.5×(tK1S+273.15))
Turbine gas velocity: cT1＝1.02×G/(FT1×10-3×ρT1)
Turbine inlet static temperature:
total temperature of turbine inlet:
turbine inlet total pressure: pT＝PT1×(tT1/t1)3.778
Turbine outlet static pressure:
turbo expansion ratio: n shapeT＝PT/PT2
Turbine adiabatic expansion work: wT＝1082×tT1×(1-1/ΠT)0.26
Adiabatic compression work of compressor:
total supercharger efficiency: etaTC＝WT/WG×0.98
6. The total efficiency of the supercharger is calculated by the software and compared with an expected value. If the opening value meets the requirement, filling the current opening value into the system; if the opening degree of the diffuser and the nozzle ring is not met, the opening degree of the diffuser and the nozzle ring is adjusted, re-testing and comparing are carried out, finally, the opening degree value meeting the requirements is obtained, the opening degree value is filled into the system, and automatic machine allocation is completed.
Finally, it is noted that the above-mentioned preferred embodiments illustrate rather than limit the invention, and that, although the invention has been described in detail with reference to the above-mentioned preferred embodiments, it will be understood by those skilled in the art that various changes in form and detail may be made therein without departing from the scope of the invention as defined by the appended claims.