CN115235746A - Method for detecting flow area of complex throttling type part - Google Patents
Method for detecting flow area of complex throttling type part Download PDFInfo
- Publication number
- CN115235746A CN115235746A CN202210843757.1A CN202210843757A CN115235746A CN 115235746 A CN115235746 A CN 115235746A CN 202210843757 A CN202210843757 A CN 202210843757A CN 115235746 A CN115235746 A CN 115235746A
- Authority
- CN
- China
- Prior art keywords
- pressure
- flow
- pressure chamber
- test
- flow area
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000034 method Methods 0.000 title abstract description 14
- 238000012360 testing method Methods 0.000 claims abstract description 43
- 238000001514 detection method Methods 0.000 claims abstract description 11
- 238000004422 calculation algorithm Methods 0.000 claims abstract description 4
- 238000013016 damping Methods 0.000 claims abstract description 4
- 238000012937 correction Methods 0.000 claims description 6
- 239000012530 fluid Substances 0.000 claims description 4
- 238000004364 calculation method Methods 0.000 claims description 3
- 239000000523 sample Substances 0.000 claims description 3
- 230000003068 static effect Effects 0.000 claims description 3
- 238000005265 energy consumption Methods 0.000 abstract description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000005259 measurement Methods 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 238000005381 potential energy Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B13/00—Measuring arrangements characterised by the use of fluids
- G01B13/20—Measuring arrangements characterised by the use of fluids for measuring areas, e.g. pneumatic planimeters
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02B—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO BUILDINGS, e.g. HOUSING, HOUSE APPLIANCES OR RELATED END-USER APPLICATIONS
- Y02B30/00—Energy efficient heating, ventilation or air conditioning [HVAC]
- Y02B30/70—Efficient control or regulation technologies, e.g. for control of refrigerant flow, motor or heating
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
本发明提供一种复杂节流类零件流通面积检测方法，包括以下步骤：风机提供的风经过多层整流阻尼网和整流栅格将气流中大的涡团打散，变成均匀流场；经过整流后气流进入压力腔，在压力腔的另一端布置需要被试的零件，试验时，设定压力腔内的需求压力，需求压力根据被试零件流通面积进行分档。当压力腔内压力低于需求压力时，提高变频电机的输入电流频率，从而提高电机及风机转速；当压力高于设定需求压力时，降低电机转速；通过比例微分积分算法，将压力腔位置在恒定压力值，记录风机转速值。得到的流通面积还需进行修正。本发明实现了对节流零件高效、高精度、低能耗的流通面积检测。
The invention provides a method for detecting the flow area of complex throttling parts, which includes the following steps: the wind provided by the fan passes through a multi-layer rectification damping net and a rectification grid to disperse large vortices in the air flow to become a uniform flow field; After rectification, the air flow enters the pressure chamber, and the parts to be tested are arranged at the other end of the pressure chamber. During the test, the required pressure in the pressure chamber is set, and the required pressure is classified according to the flow area of the tested parts. When the pressure in the pressure chamber is lower than the demand pressure, increase the input current frequency of the variable frequency motor, thereby increasing the speed of the motor and the fan; when the pressure is higher than the set demand pressure, reduce the motor speed; through the proportional, differential and integral algorithm, the pressure chamber position At a constant pressure value, record the fan speed value. The resulting flow area needs to be corrected. The invention realizes the detection of the flow area of the throttling parts with high efficiency, high precision and low energy consumption.
Description
技术领域technical field
本发明涉及一种复杂节流类零件流通面积检测方法，针对航空、航天等行业复杂节流零件流通面积检测需求，实现了对节流零件高效、高精度、低能耗的流通面积检测，属于检测技术领域。The invention relates to a method for detecting the circulation area of complex throttling parts, aiming at the detection requirements of the circulation area of complex throttling parts in aviation, aerospace and other industries, and realizing the detection of the circulation area of the throttling parts with high efficiency, high precision and low energy consumption, which belongs to detection technical field.
背景技术Background technique
涡轮是燃气涡轮发动机动力装置的核心部件之一，是将高温、高压燃气的能量转变为动能和机械能的叶轮机械。高温、高压燃气从涡轮进口流经导向叶片排转弯膨胀，将燃气势能转换为燃气动能，高速燃气通过转子叶片排发出机械功，可以由燃气涡轮轴提供给压气机进行空气压缩，压气机、燃烧室和燃气涡轮构成了燃气发生器，生成的燃气供动力涡轮作为轴功率输出或带动桨叶、风扇等，从而衍生出燃气涡轮发动机的不同类型，包括涡轴、涡浆、涡扇等。Turbine is one of the core components of the gas turbine engine power plant. It is a turbomachinery that converts the energy of high temperature and high pressure gas into kinetic energy and mechanical energy. The high-temperature and high-pressure gas flows from the turbine inlet through the guide vane row and turns and expands, converting the potential energy of the gas into the kinetic energy of the gas. The high-speed gas emits mechanical work through the rotor blades, which can be supplied by the gas turbine shaft to the compressor for air compression, compressor, combustion The gas turbine and the gas turbine constitute a gas generator, and the generated gas supplies the power turbine as a shaft power output or drives blades, fans, etc., thereby deriving different types of gas turbine engines, including turboshaft, turboprop, turbofan, etc.
在此类航空发动机、燃气涡轮工作时，燃气涡轮与动力涡轮的流通能力决定了燃烧室出口以来的高压气体膨胀比例的分配，而该比例对发动机整机性能有决定性影响，因此，涡轮的流通能力至关重要。通常而言，决定燃气涡轮、动力涡轮流通能力的关键零件为燃气涡轮、动力涡轮导向器，该零件由多片涡轮叶片组成整环的叶栅，其节流位置在相邻叶栅组成的收缩通道的最小处，其与零件的上下流道一起形成了流通面积，见附件图2、图3。工程实践表明，由于该面积形状不规则，其位置很难确定，采用直接计量的无法达到需要精度，需采用其他的技术途径。When such aero-engines and gas turbines work, the flow capacity of the gas turbine and the power turbine determines the distribution of the expansion ratio of the high-pressure gas from the outlet of the combustion chamber, and this ratio has a decisive influence on the performance of the whole engine. Therefore, the flow of the turbine Ability is critical. Generally speaking, the key parts that determine the flow capacity of gas turbines and power turbines are the guides of gas turbines and power turbines. The smallest part of the channel forms a flow area together with the upper and lower flow channels of the part, see attached Figure 2 and Figure 3. Engineering practice shows that due to the irregular shape of the area, its position is difficult to determine, and the required accuracy cannot be achieved by direct measurement, and other technical approaches must be used.
国内目前对导向流通面积(流通能力)的检测方法主要有尺寸直接计量、水流试验、流量函数试验等方法。At present, the detection methods of the guide flow area (flow capacity) in China mainly include direct measurement of size, water flow test, flow function test and other methods.
其中，尺寸直接计量是采用三坐标或光学方法对通道进行直接计量，但由于影响零件节能能力的喉部是异形的，其尺寸很小，工程实践表明，其精度达不到±1％的范围，其由于导向器叶片数多，计量效率很低，耗时长。Among them, the direct measurement of size is to use the three-coordinate or optical method to directly measure the channel, but because the throat that affects the energy-saving ability of the part is special-shaped, its size is very small, and engineering practice shows that its accuracy cannot reach the range of ± 1%. , due to the large number of guide vanes, the metering efficiency is very low, and it takes a long time.
水流试验通过建立大型的水容器，通过相同容积的水通过导向器排出的时间长短来判定零件的节流能力，该方法因为水的粘度随温度变化大、操作工对时间判断存在主观影响等原因，精度也不能满足要求。The water flow test determines the throttling capability of the part by establishing a large water container and the length of time that the same volume of water is discharged through the guide. , the accuracy can not meet the requirements.
流量函数试验是精度最高、应用最广泛的试验方法，该方法遵循流体力学中运动相似法则，通过换算模拟气流在发动机内的状态。在试验台试时，把节流件布置在下游，通过音速文氏管测量流过的气流体积流量，通过换算成质量流量，结合测量得到的进口总温、总压，计算得到流量函数值。该方法的优点是精度可到达±0.7％，可满足发动机研制的要求，但也存在很多缺点。该方法需建立独立的试验车台及高压气源站，建设成本达到数千万，单次试验时间长、试验需要参与人员多。The flow function test is the most accurate and widely used test method. This method follows the motion similarity law in fluid mechanics and simulates the state of airflow in the engine through conversion. During the test on the test bench, the throttling element is arranged downstream, and the volume flow of the air flowing through is measured through the sonic venturi, and the flow function value is calculated by converting it into mass flow and combining the measured total inlet temperature and total pressure. The advantage of this method is that the accuracy can reach ±0.7%, which can meet the requirements of engine development, but there are also many shortcomings. This method requires the establishment of an independent test bed and a high-pressure gas source station, the construction cost reaches tens of millions, the single test time is long, and the test requires many participants.
发明内容SUMMARY OF THE INVENTION
针对航空、航天等行业复杂节流零件流通面积检测需求，本发明提出一种可高效快速、高精度、低成本的复杂节流类零件有效流通面积检测方法，实现了对节流零件高效、高精度、低能耗的流通面积检测。Aiming at the detection requirements for the circulation area of complex throttling parts in aviation, aerospace and other industries, the present invention proposes a method for detecting the effective circulation area of complex throttling parts that is efficient, fast, high-precision and low-cost, and realizes efficient and high-efficiency detection of throttling parts. Accurate, low-energy flow area detection.
本发明采用常温空气为介质，以风机提供气源，通过标准孔板导向器前后的压差与风机转速直接的相关关系来计算导向器的节能能力，试验表明，该方法试验效率高、试验成本低、试验精度高。具体的技术方案为：The invention uses normal temperature air as the medium, and the fan provides the air source, and calculates the energy-saving capability of the guide through the direct correlation between the pressure difference before and after the standard orifice guide and the speed of the fan. The test shows that the method has high test efficiency and high test cost. Low and high test accuracy. The specific technical solutions are:
一种复杂节流类零件流通面积检测方法，包括以下步骤：A method for detecting the flow area of complex throttling parts, comprising the following steps:
(1)变频电机驱动风机产生大流量的风量，提供风压头；(1) The variable frequency motor drives the fan to generate a large flow of air and provide air pressure head;
(2)风机提供的风经过多层整流阻尼网和整流栅格将气流中大的涡团打散，变成压力均匀、且有湍流度的流场；(2) The wind provided by the fan passes through the multi-layer rectification damping net and the rectification grid to disperse the large vortex in the airflow, turning it into a flow field with uniform pressure and turbulence;
经过整流后气流进入压力腔，在压力腔中布置有温度、压力探针，测量压力腔中的温度及静压值；After rectification, the air flow enters the pressure chamber, and the temperature and pressure probes are arranged in the pressure chamber to measure the temperature and static pressure in the pressure chamber;
在压力腔的另一端布置需要被试的零件，压力腔内的气流由此排入大气；The parts to be tested are arranged at the other end of the pressure chamber, and the air flow in the pressure chamber is discharged into the atmosphere;
试验时，设定压力腔内的需求压力，需求压力根据被试零件流通面积进行分档。当压力腔内压力低于需求压力时，提高变频电机的输入电流频率，从而提高电机及风机转速，达到增大风量风压的目的；当压力高于设定需求压力时，降低电机转速；During the test, the demand pressure in the pressure chamber is set, and the demand pressure is classified according to the flow area of the tested part. When the pressure in the pressure chamber is lower than the demand pressure, increase the input current frequency of the variable frequency motor, thereby increasing the speed of the motor and the fan, to achieve the purpose of increasing the air volume and pressure; when the pressure is higher than the set demand pressure, reduce the motor speed;
(3)通过比例微分积分算法，将压力腔位置在恒定压力值。此时，记录风机转速值。(3) Through the proportional-differential-integration algorithm, the position of the pressure chamber is set at a constant pressure value. At this time, record the fan speed value.
试验采用一组已知节流面积的标准孔板或其他节流元件进行校准，得到压力、转速及面积的对应关系。被试零件则由试验得到的设定压力下的转速值进行插值，得到流通面积。The test uses a set of standard orifice plates or other throttling elements with known throttling areas to calibrate, and obtain the corresponding relationship between pressure, speed and area. The tested part is interpolated from the rotational speed value under the set pressure obtained by the test to obtain the flow area.
步骤(3)中，试验测试的参数还包括大气压力、大气温度、压力腔室温度、整流前端压力、气体排出温度、大气湿度。In step (3), the parameters tested by the test also include atmospheric pressure, atmospheric temperature, pressure chamber temperature, rectification front-end pressure, gas discharge temperature, and atmospheric humidity.
(4)试验得到的流通面积还需进行修正。开展流通系数的修正。其中需由测试参数计算得到试验件流场的雷诺数值；(4) The flow area obtained by the test needs to be corrected. Carry out the correction of the flow coefficient. Among them, the Reynolds value of the flow field of the test piece needs to be calculated from the test parameters;
步骤(4)中，雷诺数计算公式如下：In step (4), the Reynolds number calculation formula is as follows:
Re＝ρvL/μRe=ρvL/μ
ρ、μ为流体密度和动力粘性系数，v、L为流场的特征速度和特征长度。雷诺数物理上表示惯性力和粘性力量级的比。特征长度取孔板直径，出口气流速度由大气压与恒定压力腔室压力计算。ρ and μ are the fluid density and dynamic viscosity coefficient, and v and L are the characteristic velocity and characteristic length of the flow field. The Reynolds number physically expresses the ratio of inertial and viscous force levels. The characteristic length is taken as the diameter of the orifice plate, and the outlet air velocity is calculated from the atmospheric pressure and the constant pressure chamber pressure.
通过雷诺数计算流量系数，在孔板已知物理面积的基础上开展修正，从而得到有效流通面积The flow coefficient is calculated by the Reynolds number, and the correction is carried out on the basis of the known physical area of the orifice plate, so as to obtain the effective flow area
本发明技术方案带来的有益效果：The beneficial effects brought by the technical solution of the present invention:
本发明试验设计占地面积小，投资成本低，可移动；The test design of the invention has small footprint, low investment cost and can be moved;
按本发明生成的试验设备对零件流通面积的测试精度高，达到±0.5％；The test equipment generated according to the invention has high test accuracy for the flow area of parts, reaching ±0.5%;
按本发明生成的试验设备试验成本低，操作人员只需要1个，费用低；The test equipment generated according to the invention has low test cost, only one operator is needed, and the cost is low;
本发明试验设备试验零件面积范围大，可根据要求进行定制；The test equipment of the invention has a large area of test parts and can be customized according to requirements;
按本发明方法生成的设备维护成本低。The equipment produced according to the method of the present invention has low maintenance costs.
附图说明Description of drawings
图1是本发明的技术方案示意图；Fig. 1 is the technical scheme schematic diagram of the present invention;
图2为典型涡轮导向器示意图，由上下流道及叶片组成的叶栅通道组成。Figure 2 is a schematic diagram of a typical turbine guide, which is composed of an upper and lower flow channel and a cascade channel composed of blades.
图3为气流流过涡轮导向器在叶栅截面的示意图，气流在叶栅通道中加速，最小的位置为喉部。Figure 3 is a schematic diagram of the airflow passing through the turbine guide in the cascade section, the airflow is accelerated in the cascade channel, and the smallest position is the throat.
具体实施方式Detailed ways
结合实施例说明本发明的具体技术方案。The specific technical solutions of the present invention are described with reference to the embodiments.
如图1所示，一种复杂节流类零件流通面积检测方法，包括以下步骤：As shown in Figure 1, a method for detecting the flow area of complex throttling parts includes the following steps:
(1)变频电机驱动风机产生大流量的风量，提供风压头；(1) The variable frequency motor drives the fan to generate a large flow of air and provide air pressure head;
(2)风机提供的风经过多层整流阻尼网和整流栅格将气流中大的涡团打散，变成压力均匀、且有湍流度的流场；(2) The wind provided by the fan passes through the multi-layer rectification damping net and the rectification grid to disperse the large vortex in the airflow, turning it into a flow field with uniform pressure and turbulence;
经过整流后气流进入压力腔，在压力腔中布置有温度、压力探针，测量压力腔中的温度及静压值；After rectification, the air flow enters the pressure chamber, and the temperature and pressure probes are arranged in the pressure chamber to measure the temperature and static pressure in the pressure chamber;
在压力腔的另一端布置需要被试的零件，压力腔内的气流由此排入大气；The parts to be tested are arranged at the other end of the pressure chamber, and the air flow in the pressure chamber is discharged into the atmosphere;
试验时，设定压力腔内的需求压力，需求压力根据被试零件流通面积进行分档。当压力腔内压力低于需求压力时，通过可编程逻辑控制器(PLC),提高变频电机的输入电流频率，从而提高电机及风机转速，达到增大风量风压的目的；当压力高于设定需求压力时，降低电机转速。During the test, the demand pressure in the pressure chamber is set, and the demand pressure is classified according to the flow area of the tested part. When the pressure in the pressure chamber is lower than the required pressure, the input current frequency of the variable frequency motor is increased through the programmable logic controller (PLC), thereby increasing the speed of the motor and the fan to achieve the purpose of increasing the air volume and air pressure; when the pressure is higher than the set value When the demand pressure is fixed, reduce the motor speed.
(3)通过比例微分积分(PID)算法，将压力腔位置在恒定压力值。此时，记录风机转速值。(3) Through the proportional derivative integral (PID) algorithm, the position of the pressure chamber is at a constant pressure value. At this time, record the fan speed value.
于此同时，试验测试的参数主要还包括大气压力、大气温度、压力腔室温度、整流前端压力、气体排出温度、大气湿度等。At the same time, the test parameters mainly include atmospheric pressure, atmospheric temperature, pressure chamber temperature, rectification front-end pressure, gas discharge temperature, atmospheric humidity, etc.
试验采用一组已知节流面积的标准孔板或其他节流元件进行校准，得到压力、转速及面积的对应关系。被试零件则由试验得到的设定压力下的转速值进行插值，得到流通面积。The test uses a set of standard orifice plates or other throttling elements with known throttling areas to calibrate, and obtain the corresponding relationship between pressure, speed and area. The tested part is interpolated from the rotational speed value under the set pressure obtained by the test to obtain the flow area.
(4)试验得到的流通面积还需进行修正。由于不同零件在不同压力、大气条件下的气流状态不同，因此还需开展流通系数的修正。其中需由测试参数计算得到试验件流场的雷诺数值。雷诺数计算公式如下：(4) The flow area obtained by the test needs to be corrected. Due to the different air flow states of different parts under different pressure and atmospheric conditions, it is also necessary to carry out the correction of the flow coefficient. Among them, the Reynolds value of the flow field of the test piece needs to be calculated from the test parameters. The formula for calculating the Reynolds number is as follows:
Re＝ρvL/μRe=ρvL/μ
ρ、μ为流体密度和动力粘性系数，v、L为流场的特征速度和特征长度。雷诺数物理上表示惯性力和粘性力量级的比。这里的特征长度取孔板直径，出口气流速度由大气压与恒定压力腔室压力计算。ρ and μ are the fluid density and dynamic viscosity coefficient, and v and L are the characteristic velocity and characteristic length of the flow field. The Reynolds number physically expresses the ratio of inertial and viscous force levels. The characteristic length here is taken as the diameter of the orifice plate, and the outlet air velocity is calculated from the atmospheric pressure and the constant pressure chamber pressure.
通过雷诺数计算流量系数，在孔板已知物理面积的基础上开展修正，从而得到有效流通面积。The flow coefficient is calculated by the Reynolds number, and the correction is carried out on the basis of the known physical area of the orifice plate to obtain the effective flow area.
Claims (3)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210843757.1A CN115235746A (en) | 2022-07-18 | 2022-07-18 | Method for detecting flow area of complex throttling type part |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210843757.1A CN115235746A (en) | 2022-07-18 | 2022-07-18 | Method for detecting flow area of complex throttling type part |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115235746A true CN115235746A (en) | 2022-10-25 |
Family
ID=83674003
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210843757.1A Pending CN115235746A (en) | 2022-07-18 | 2022-07-18 | Method for detecting flow area of complex throttling type part |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115235746A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07159208A (en) * | 1993-10-16 | 1995-06-23 | Iwk Regler & Kompensatoren Gmbh | Method and device for determining flow rate m of fluid in duct |
| CN105043335A (en) * | 2015-09-10 | 2015-11-11 | 成都国营锦江机器厂 | Turbine guider channel area measuring instrument |
| CN109974634A (en) * | 2019-03-25 | 2019-07-05 | 湖南工业大学 | Test method and test system for throat area or medium flow area of special-shaped structural parts |
| US20190384888A1 (en) * | 2018-06-13 | 2019-12-19 | Dalian University Of Technology | Methodology for a modeling starting process of a micro gas turbine engine |
| CN111914362A (en) * | 2020-07-22 | 2020-11-10 | 中国航发沈阳发动机研究所 | Self-adaptive method for turbofan engine model in research and development stage |
| CN113607420A (en) * | 2021-08-17 | 2021-11-05 | 中国航发贵阳发动机设计研究所 | A low-pressure turbine guide ring blowing test installation structure and test method |
-
2022
- 2022-07-18 CN CN202210843757.1A patent/CN115235746A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07159208A (en) * | 1993-10-16 | 1995-06-23 | Iwk Regler & Kompensatoren Gmbh | Method and device for determining flow rate m of fluid in duct |
| CN105043335A (en) * | 2015-09-10 | 2015-11-11 | 成都国营锦江机器厂 | Turbine guider channel area measuring instrument |
| US20190384888A1 (en) * | 2018-06-13 | 2019-12-19 | Dalian University Of Technology | Methodology for a modeling starting process of a micro gas turbine engine |
| CN109974634A (en) * | 2019-03-25 | 2019-07-05 | 湖南工业大学 | Test method and test system for throat area or medium flow area of special-shaped structural parts |
| CN111914362A (en) * | 2020-07-22 | 2020-11-10 | 中国航发沈阳发动机研究所 | Self-adaptive method for turbofan engine model in research and development stage |
| CN113607420A (en) * | 2021-08-17 | 2021-11-05 | 中国航发贵阳发动机设计研究所 | A low-pressure turbine guide ring blowing test installation structure and test method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Wright | Fluid machinery: performance, analysis, and design | |
| CN106198034B (en) | A rotary ram compressor test system | |
| CN102589894B (en) | Combined Micro Compressor/Turbine Test Bench and Test Method | |
| CN105738116B (en) | A kind of turbine test device | |
| CN110726562B (en) | An experimental research device for optimal matching of diffuser and flame tube | |
| Hajilouy-Benisi et al. | Flow and performance characteristics of twin-entry radial turbine under full and extreme partial admission conditions | |
| Gravdahl et al. | Modeling for surge control of centrifugal compressors: Comparison with experiment | |
| Lou et al. | Development of a centrifugal compressor facility for performance and aeromechanics research | |
| Chen et al. | Pressure drop analysis and aerodynamic design of compressor L-inlet duct | |
| Schobeiri et al. | Aerodynamic and performance studies of a three-stage high pressure research turbine with 3-D-blades, design point and off-design experimental investigations | |
| CN113623027B (en) | Exhaust diffuser experiment table capable of performing steady-state and transition-state tests | |
| Rehder et al. | Next generation turbine testing at DLR | |
| US20240418175A1 (en) | Performance test bench device for centrifugal compressor under variable working condition of engine | |
| CN113153458B (en) | Dynamic testing system and method for stationary blade heating and dehumidification | |
| Li et al. | Effect of rotor-stator axial gap on the tip seal leakage flow of a steam turbine | |
| CN109443782A (en) | A kind of device of the air-cooled turbine guide vane cooling air stream measurement of aero-engine | |
| Fu et al. | Experimental and numerical investigation of interaction between turbine stage and exhaust hood | |
| Schleer et al. | Influence of geometric scaling on the stability and range of a turbocharger centrifugal compressor | |
| Lange et al. | An experimental investigation of shrouded and cantilevered compressor stators at varying clearance sizes | |
| CN115235746A (en) | Method for detecting flow area of complex throttling type part | |
| Kormanik et al. | Purdue 3-stage axial compressor research facility: Through the years, to infinity, and beyond | |
| Brossman et al. | Tailoring inlet flow to enable high accuracy compressor performance measurements | |
| Deng et al. | Experimental and numerical investigation on overall performance of a radial inflow turbine for 100kW mircoturbine | |
| Diehl | Mitigation of tip leakage induced phenomena in a low Reynolds number centrifugal compressor via blade loading distribution | |
| Johansson et al. | Aerodynamic and heat transfer measurements on an intermediate turbine duct vane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |