A New Micro Turbo-Machinery Test Facility

2010 ◽  
Author(s):  
Chen Xia ◽  
Guoping Huang ◽  
Jie Chen
Keyword(s):  
Mass Flow ◽  
High Speed ◽  
Modular Design ◽  
Thermal Protection ◽  
Dynamic Pressure ◽  
Pressure Sensors ◽  
Test Facility ◽  
Inlet Temperature ◽  
Test Bed ◽  
Turbo Machinery

The design and construction of a new test facility of micro turbo-machinery are presented for micro centrifugal compressors and radial turbines. The bed can be used for the full speed compressor test and the long duration hot turbine test. In order to adjust the testing condition rapidly, all the regulations of operating state are completed automatically by the control system. The test bed can be used for testing impeller performance with a series of diameter from 55 to 180 mm as a result of the modular design. A thermal protection system is designed to avoid the heat distortion caused by the high inlet temperature of turbine which may exceeds 1100K and provide a proper experimental environment for the electronic components. A photoelectric torque transducer with an accuracy of 1% is designed to measure the torque of a rigid shaft at a high speed over 120000rpm, and the maximum shaft torque is 7.7 N·m. The pressure and temperature are measured by pressure probes and thermocouples. The dynamic pressure signal of the centrifugal compressor is monitored by dynamic pressure sensors. The V-cone pressure-difference mass-flow meters are used for measuring mass-flow. The maximum rotating speed is 125000rpm, and the mass flow adjusted by the electric control valves varies from 0.1 to 1.0 kg/sec. The maximum inlet total temperature of the turbine is 1180K.

Experimental Inverstigations On the Pressure Fluctuations in the Sealing Gap of Dry Gas Seals with Embedded Pressure Sensors

2021 ◽  
Author(s):  
Jingjing Luo ◽  
Dieter Brillert
Keyword(s):  
High Speed ◽  
Gas Flow ◽  
Static Pressure ◽  
Pressure Sensors ◽  
Operating Conditions ◽  
Test Facility ◽  
Experimental Investigations ◽  
Mechanical Seals ◽  
Process Gas ◽  
Sealing Gap

Abstract Dry gas lubricated non-contacting mechanical seals (DGS), most commonly found in centrifugal compressors, prevent the process gas flow into the atmosphere. Especially when high speed is combined with high pressure, DGS is the preferred choice over other sealing alternatives. In order to investigate the flow field in the sealing gap and to facilitate the numerical prediction of the seal performance, a dedicated test facility is developed to carry out the measurement of key parameters in the gas film. Gas in the sealing film varies according to the seal inlet pressure, and the thickness of gas film depends on this fluctuated pressure. In this paper, the test facility, measurement methods and the first results of static pressure measurements in the sealing gap of the DGS obtained in the described test facility are presented. An industry DGS with three-dimensional grooves on the surface of the rotating ring, where experimental investigations take place, is used. The static pressure in the gas film is measured, up to 20 bar and 8,100 rpm, by several high frequency ultraminiature pressure transducers embedded into the stationary ring. The experimental results are discussed and compared with the numerical model programmed in MATLAB, the characteristic and magnitude of which have a good agreement with the numerical simulations. It suggests the feasibility of measuring pressure profiles of the standard industry DGS under pressurized dynamic operating conditions without altering the key components of the seal and thereby affecting the seal performance.

Spark Ignition of SPP Injector Under Sub-Atmospheric Conditions

2021 ◽  
Author(s):  
Qianpeng Zhao ◽  
Yong Mu ◽  
Jinhu Yang ◽  
Yulan Wang ◽  
Gang Xu
Keyword(s):  
High Speed ◽  
Spark Ignition ◽  
Test Facility ◽  
Propagation Mode ◽  
Inlet Temperature ◽  
Reacting Flow ◽  
Atmospheric Conditions ◽  
Flame Kernel ◽  
Flame Development ◽  
Initial Flame

Abstract The sub-atmospheric ignition performance of an SPP (Stratified Partially Premixed) injector and combustor is investigated experimentally on the high-altitude test facility. In order to explore the influence of sub-atmospheric pressure on reignition performance and flame propagation mode, experiments are conducted under different pressures ranging from 19 kPa to 101 kPa. The inlet temperature and pressure drop of the injector (ΔPsw/P3t) are kept constant at 303 K and 3% respectively. The transparent quartz window mounted on the sidewall of the model combustor provides optical access of flame signals. Ignition fuel-air ratio (FAR) under different inlet pressures are experimentally acquired. The spark ignition processes, including the formation of flame kernel, the flame development and stabilization are recorded by a high-speed camera at a rate of 5kHz. Experimental results indicate that the minimum ignition FAR grows rapidly as the inlet air pressure decreases. An algorithm is developed to track the trajectory of flame kernels within 25ms following the spark during its breakup and motion processes. Results show that the calculated trajectory provides a clear description of the flame evolution process. Under different inlet air pressures, the propagation trajectories of flame kernels share similarities in initial phase. It is pivotal for a successful ignition that the initial flame kernel keeps enough intensity and moves into CTRZ (Center-Toroidal Recirculation Zone) along radial direction. Finally, the time-averaged non-reacting flow field under inlet pressure of 54kPa and fuel mass flow of 8kg/h is simulated. The effects of flow structure and fuel spatial distribution on kernel propagation and flame evolution are analyzed.

A Novel, High-Frequency, Reciprocal Calibration Method for Dynamic Pressure Sensors Used in High-Speed Flows

2020 ◽  
Author(s):  
David A. Mills ◽  
Tai-An Chen ◽  
Stephen Horowitz ◽  
William Patterson ◽  
Mark Sheplak
Keyword(s):  
High Frequency ◽  
High Speed ◽  
Dynamic Pressure ◽  
Pressure Sensors ◽  
Calibration Method ◽  
High Speed Flows

Initial Operating Experience and Test Results of ABB’s Gas Turbine GT13E2

1995 ◽  
Author(s):  
M. Klohr ◽  
J. Schmidtke ◽  
S. Tschirren ◽  
P. Rihak
Keyword(s):  
Gas Turbine ◽  
Dynamic Pressure ◽  
Operating Experience ◽  
Combined Cycle ◽  
Test Facility ◽  
Vibration Velocity ◽  
Inlet Temperature ◽  
Test Results ◽  
Pressure System ◽  
Annular Combustor

On 20 October 1993, the first ABB GT13E2 gas turbine was put into operation. This 165 MW class gas turbine achieves 35,7% thermal efficiency in single cycle application and up to 54,3% (according ISO standard 3977, Annexe F) in a three pressure system. An optimised turbine and compressor design along with the increased turbine inlet temperature, lead to improved efficiency and electrical output. A new concept for the combustor aimed at meeting the increasing demands on gas turbine emissions. The GT13E2 is equipped with the new single annular combustor and 72 of the ABB EV double cone burners. The commissioning and testing of the first GT13E2 was carried out at the Kawasaki Gas Turbine Research Center (KGRC) in Sodegaura City near Tokyo, Japan. The gas turbine was assembled with various measurement systems to monitor static and dynamic pressure, gas and metal temperature, expansion, vibration, velocity and emissions. The facility will be used during a 15 year joint test program by ABB and Kawasaki Heavy Industries (KHI) to obtain a sound database of operating experience for further improvements of the GT13E2 gas turbine. Therefore, mid 1994 a second test phase was conducted and early 1995 a third test period is scheduled. In parallel, the 2nd and 3rd GT13E2’s were commissioned and tested at the Deeside Combined Cycle Power Plant near Chester, Great Britain. In November 1994, the 4th GT13E2 at Lage Weide was successfully commissioned. This paper describes the operating experience with the GT13E2 during the first commissioning and test phases at KGRC and Deeside. The design features, the test facility, the instrumentation, the commissioning and test results are presented and discussed.

Durability Surveillance of Advanced Gas Turbines: Performance and Mechanical Baseline Development for the GE Frame 7F

1993 ◽  
Author(s):  
Cyrus B. Meher-Homji ◽  
A. N. Lakshminarasimha ◽  
G. Mani ◽  
Clark V. Dohner ◽  
Igor Ondryas ◽  
...  
Keyword(s):  
Electric Power ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Dynamic Pressure ◽  
Pressure Sensors ◽  
Practical Interest ◽  
Advanced Technology ◽  
Surveillance Program ◽  
Inlet Temperature ◽  
Base Line

This paper describes the methodology and approach of baseline development as part of a comprehensive Durability Surveillance Study Program of an Advanced Gas Turbine (AGT) sponsored by the Electric Power Research Institute (EPRI) on a GE Frame 7F gas turbine operating in peaking service. The gas turbine is an advanced technology 156 MW (ISO), 955 lb/sec machine operating at a turbine inlet temperature of 2300° F (rotor inlet temperature) and a pressure ratio of 13.5:1. The turbine is located at Potomac Electric Power Company (PEPCO) Station H plant in Dickerson, Maryland. In order to facilitate the durability surveillance, the turbine has a data acquisition and analysis system which obtains data from the control system (via serial port) as well as from special sensors such as proximity probes, dynamic pressure sensors, strain gauges and hot section pyrometers. With the GE Frame 7F and FA machines becoming very popular in utility applications worldwide, the EPRI Durability Surveillance Program and baseline generation methodology will be of considerable practical interest to gas turbine users. The basic methodology presented for baseline development can be used for any single shaft gas turbine. We believe the base-line to be of considerable importance in evaluating future condition of the machine as well as for maintenance planning. The paper also briefly describes the status and future plans of the EPRI durability surveillance program.

Experimental Investigations on the Pressure Fluctuations in the Sealing Gap of Dry Gas Seals With Embedded Pressure Sensors

2020 ◽  
Author(s):  
Jingjing Luo ◽  
Dieter Brillert
Keyword(s):  
High Speed ◽  
Gas Flow ◽  
Static Pressure ◽  
Pressure Sensors ◽  
Operating Conditions ◽  
Test Facility ◽  
Experimental Investigations ◽  
Mechanical Seals ◽  
Process Gas ◽  
Sealing Gap

Abstract Dry gas lubricated non-contacting mechanical seals (DGS), most commonly found in centrifugal compressors, prevent the process gas flow into the atmosphere. Especially when high speed is combined with high pressure, DGS is the preferred choice over other sealing alternatives. Even though the non-contacting seal is proved reliable; the ultra-thin gas film can still lead to a host of potential problems due to possible contact. In order to investigate the flow field in the sealing gap and to facilitate the numerical prediction of the seal performance, a dedicated test facility is developed to carry out the measurement of key parameters in the gas film. Gas in the sealing film varies according to the seal inlet pressure, and the thickness of gas film depends on this fluctuated pressure. In this paper, the test facility, measurement methods and the first results of static pressure measurements in the sealing gap of the DGS obtained in the described test facility are presented. An industry DGS with three-dimensional grooves on the surface of the rotating ring, where experimental investigations take place, is used. The static pressure in the gas film is measured, up to 20 bar and 8,100 rpm, by several high frequency ultraminiature pressure transducers embedded into the stationary ring. The experimental results are discussed and compared with the numerical model programmed in MATLAB [1], the characteristic and magnitude of which have a good agreement with the numerical simulations. It suggests the feasibility of measuring pressure profiles of the standard industry DGS under pressurized dynamic operating conditions without altering the key components of the seal and thereby affecting the seal performance.

Experimental and Numerical Flutter Investigation of the 1st Stage Rotor in 4-Stage High Speed Compressor

2008 ◽  
Author(s):  
E. Johann ◽  
B. Mu¨ck ◽  
J. Nipkau
Keyword(s):  
High Speed ◽  
Dynamic Pressure ◽  
Experimental Tests ◽  
Rotor Blades ◽  
Test Facility ◽  
Nodal Diameter ◽  
Pressure Transducers ◽  
Multistage Compressor ◽  
Set Up ◽  
Forced Responses

Experimental tests were performed to investigate flutter behaviour of the transonic rotor in a high-speed multistage compressor test facility. Besides the acquisition of overall performance parameters the rig was equipped with special instrumentation such as strain gauges, tip-timing system and dynamic pressure transducers. The 4-stage compressor comprises 3 variable vanes. The instrumentation was able to measure stall and flutter and forced responses of the rotor blades. The experimental data was used to validate the in-house aeroelastic solver. During testing flutter was triggered intentionally at part speed conditions with malscheduled variable vanes. The malschedule changed the flow incidences for the relevant rotor and induced flutter. An aeroelastic simulation was set up according to the flutter conditions found during the experiment. The measured boundary conditions were used to set up the aeroelastic simulation. The calculation shows the torsion mode with a negative aerodynamic damping which confirms the test results. The only difference between test and prediction is the nodal diameter, at which the flutter occurs.

An Experimental Study of Liquid Flooding in Vertical Large Scale Rectangular Channel With the Counter-Current Flow of Air and Water Film

2018 ◽  
Author(s):  
Kashuai Du ◽  
Po Hu ◽  
Shuwei Zhai ◽  
Xiaojie Yang ◽  
Weibo Wang
Keyword(s):  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
High Speed ◽  
Influence Factor ◽  
Rectangular Channel ◽  
Water Film ◽  
Test Facility ◽  
Film Rupture ◽  
Counter Current

In the present study, a test facility, called WAFT [1], has been set up to study liquid flooding phenomena on a heated large flat plate with the counter-current air-water flow. The various thermal hydraulic working condition parameters, especially, temperature and velocity of water, air and oil media, could be obtained by adjust the control devices, such as, heater, valve and frequency regulator. Because of transparent organic glass slab in the test section, the dynamic behavior of water film flow in the different locations of test area can be clearly observed by virtue of high-speed video camera, such as wave pattern change, film rupture, droplet splash and dry spot occurrence. During the test, a series of tests were performed under the conditions of steel plate heat flux 25 kw/m2, the water film with mass flow rate 0.1 and 0.6 kg/s.m and the temperature 70 and 92 °C, the velocity of air entrance ranging from 6.0 to 11.50 m/s and the inlet air temperature of 45 and 60 °C, respectively. According to the acquisition data, a modified Wallis liquid flooding predicted relation was proposed considering the influence factor of temperature from large steel plates, air and water film, i.e., the effect of water film evaporation. The results indicate that the mass flow rate of water film and inlet air velocity have a great effect on the emergence of liquid flooding.

Study of buzz phenomenon using visualization of external shock structure

2018 ◽  
Vol 233 (7) ◽  
pp. 2690-2698 ◽  
Author(s):  
M Farahani ◽  
A Jaberi
Keyword(s):  
Mass Flow ◽  
High Speed ◽  
Pressure Sensors ◽  
Shock Structure ◽  
The Body ◽  
External Compression ◽  
Mass Flow Rates ◽  
Shock Motion ◽  
Shock Oscillation ◽  
Visual Description

An experimental study was carried out on an axisymmetric supersonic inlet with external compression in order to investigate the buzz phenomenon at different angles of attack and mass flow rates. The model was equipped with accurate and high-frequency pressure sensors, and the tests were conducted at Mach numbers varying from 1.8 to 2.5, for various angles of attack. Shadowgraph visualization technique, together with a high-speed camera, was used to provide the visual description of the shock structure in front of the inlet and to study the characteristics of buzz. Furthermore, pressure distribution over the spike surface was measured using several pressure sensors. Frequency of the buzz and shock displacement were measured by inspection of visualization pictures in each test. The obtained data from shadowgraphs were compared with those obtained from pressure measurements, and good agreement was found between them. The results revealed that for a moderate value of mass flow rate, the frequency of shock oscillation decreases as Mach number increases. Further, by increasing angle of attack, the shock displacement of oscillation will increase. At non-zero angles of attack, the displacement and frequency of shock motion show different behaviors on the leeward and windward sides of the body.

scholarly journals Temperature Profile in Rubber Injection Molding: Application of a Recently Developed Testing Method to Improve the Process Simulation and Calculation of Curing Kinetics

Polymers ◽  
2021 ◽  
Vol 13 (3) ◽  
pp. 380
Author(s):  
Martin Traintinger ◽  
Roman Christopher Kerschbaumer ◽  
Bernhard Lechner ◽  
Walter Friesenbichler ◽  
Thomas Lucyshyn
Keyword(s):  
Injection Molding ◽  
Temperature Profile ◽  
Pressure Sensors ◽  
Simulation Software ◽  
Relative Degree ◽  
Actual State ◽  
Process Conditions ◽  
Inlet Temperature ◽  
Degree Of Cure ◽  
Mass Temperature

Injection molding of rubber compounds is an easily conducted yet sophisticated method for rubber processing. Simulation software is used to examine the optimal process conditions, identify failure scenarios, and save resources. Due to the complexity of the entire process, various aspects have to be considered in the numerical approach. This contribution focused on a comparison of process simulations with various definitions of the material’s inlet temperature, ranging from a stepwise increase, but constant temperature, to an exact axial mass temperature profile prior to injection. The latter was obtained with a specially designed, unique test stand consisting of a plasticizing cylinder equipped with pressure sensors, a throttle valve for pressure adjustments, and a measurement bar with thermocouples for the determination of the actual state of the mass temperature. For the verification of the theoretical calculations, practical experiments were conducted on a rubber injection molding machine equipped with the mold used in the simulation. The moldings, obtained at different vulcanization time, were characterized mechanically and the results were normalized to a relative degree of cure in order to enable comparison of the real process and the simulation. Considering the actual state of the mass temperature, the simulation showed an excellent correlation of the measured and calculated mass temperatures in the cold runner. Additionally, the relative degree of cure was closer to reality when the mass temperature profile after dosing was applied in the simulation.

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