The Measurement and Process of Aeroengine Inlet Total Pressure Field

2011 ◽  
Vol 383-390 ◽  
pp. 4323-4328
Author(s):  
Xun Yang ◽  
Yong Lei
Keyword(s):  
Total Pressure ◽  
Integral Method ◽  
Pressure Field ◽  
Averaging Method ◽  
Test Scheme ◽  
Test Results ◽  
Ring Segment ◽  
Test Points ◽  
Radial Average ◽  
Ring Boundary

It’s important to measure inlet total pressure field for aeroengine. Firstly, test scheme is discussed. Three pectinate total pressure probes, which can be rotated with an additional straight ring segment around the engine axis, are used to measure the total pressure field. The radial distribution of test points is designed via Tchebycheff integral method. Radial average and circumferential average are calculated according to the field data via area averaging method. At last the total pressure field is visualized via mapping the data to colors. Test results show that the total pressure distribution in main airflow is evener than that in boundary layers and the thickness of inner and outer ring boundary layer can be estimated.

Influence and Analysis of Temperature Rise to Principal Spindle's Rotating Error Test

2013 ◽  
Vol 380-384 ◽  
pp. 101-104
Author(s):  
Kuo Liu ◽  
Jian Feng Lin ◽  
Yue Wu Wang ◽  
Tie Jun Zhu
Keyword(s):  
Test Method ◽  
Test Scheme ◽  
Test Results ◽  
Machine Center ◽  
Rotating Speed ◽  
Speed Test ◽  
Dynamic Errors ◽  
Machine Centers ◽  
Radial Average ◽  
Scientific Test

The form of principal spindle's dynamic errors is analysed firstly. Scientific test scheme is designed to analyse the influence of rotating speed to rotating errors and decrease temperature rises influence. Principal spindle's radial average errors and asynchronous errors, axial average errors and asynchronous errors, minimum radial separation center of some vertical machine center are all tested with SPN-300 of API. Test method is rise speed-test-stop & cooling-rise speed. Three vertical machine centers are tested and every machine center is tested three times at different rotating speed. The test results and the influences of all errors are analysed at last.

scholarly journals Ride through testing of variable speed drive due to voltage sag types (types I, II and III)

2019 ◽  
Vol 10 (2) ◽  
pp. 690
Author(s):  
Surya Hardi ◽  
R. Harahap ◽  
S. Ahmad ◽  
M. Isa
Keyword(s):  
Drop Out ◽  
Dropping Out ◽  
Voltage Sag ◽  
Type I ◽  
Voltage Sags ◽  
Test Results ◽  
Variable Speed ◽  
Variable Speed Drives ◽  
Standard Curve ◽  
Test Points

Variable speed drives (VSDs) are widely used in various applications mainly in process industry need constant rotational speed. It is developed from power electronic components thus saving energy in its operation. Unfortunately it is susceptible against power quality problem for example voltage sags. The VSD may be disruption or drop out when it is supplied by voltage sags and it is determined by sag characteristics. This study is to investigate effect of voltage sags Types I, II and III on VSD through laboratory testing. The voltage sags characteristics are generated from voltage sag generator (Shaffner 2100 EMC).  The effects are presented in susceptibility curves in disruption and drop out conditions. The curves resulted are evaluated by standard curve recommended. Test results show that voltage sag Type I cause the VSD disruption only, whereas two types sag other result in the VSD disruption and also drop out. Evaluation results explain  a few test points are in operation area for disruption condition whereas test points for dropping out far below the threshold recommended. Hence the VSD has good quality to voltage sags.

Flow field behind a complex total pressure distortion screen

2019 ◽  
Vol 233 (14) ◽  
pp. 5075-5092
Author(s):  
M Sivapragasam
Keyword(s):  
Flow Field ◽  
Total Pressure ◽  
Design Methodology ◽  
Pressure Field ◽  
Alternative Interpretation ◽  
Interface Plane ◽  
Screen Design ◽  
Pressure Distributions ◽  
Water Jet Cutting ◽  
Distortion Index

The flow field behind a complex total pressure distortion screen is investigated experimentally and numerically. The distortion screen is designed using an established design methodology and fabricated by water-jet cutting technique. The distorted total pressure field behind the screen is quantified by a distortion index parameter, which is evaluated from computations and experiments for several values of inlet Mach number. The root-mean-square error between the target total pressure values and that achieved by the screen design at the aerodynamic interface plane is 4.75%. The evolution of the distorted total pressure field downstream of the screen is presented in detail in terms of radial and circumferential total pressure distributions and their gradients. An alternative interpretation of the distorted total pressure field is made by means of defining a total pressure flux existing behind the screen and expanding it using derivative-moment transformation technique. It is seen that the circumferential vorticity is a major contributing factor to the total pressure flux.

Design and Test Results of a Ultra High Loaded Single Stage High Pressure Turbine

2013 ◽  
Author(s):  
Harjit S. Hura ◽  
Scott Carson ◽  
Rob Saeidi ◽  
Hyoun-Woo Shin ◽  
Paul Giel
Keyword(s):  
High Pressure ◽  
Total Pressure ◽  
High Speed ◽  
Pressure Ratio ◽  
Single Stage ◽  
Test Results ◽  
High Pressure Turbine ◽  
Technology Program ◽  
High Pressure Ratio ◽  
Expected Performance

This paper describes the engine and rig design, and test results of an ultra-highly loaded single stage high pressure turbine. In service aviation single stage HPTs typically operate at a total-to-total pressure ratio of less than 4.0. At higher pressure ratios or energy extraction the nozzle and blade both have regions of supersonic flow and shock structures which, if not mitigated, can result in a large loss in efficiency both in the turbine itself and due to interaction with the downstream component which may be a turbine center frame or a low pressure turbine. Extending the viability of the single stage HPT to higher pressure ratios is attractive as it enables a compact engine with less weight, and lower initial and maintenance costs as compared to a two stage HPT. The present work was performed as part of the NASA UEET (Ultra-Efficient Engine Technology) program from 2002 through 2005. The goal of the program was to design and rig test a cooled single stage HPT with a pressure ratio of 5.5 with an efficiency at least two points higher than the state of the art. Preliminary design tools and a design of experiments approach were used to design the flow path. Stage loading and through-flow were set at appropriate levels based on prior experience on high pressure ratio single stage turbines. Appropriate choices of blade aspect ratio, count, and reaction were made based on comparison with similar HPT designs. A low shock blading design approach was used to minimize the shock strength in the blade during design iterations. CFD calculations were made to assess performance. The HPT aerodynamics and cooling design was replicated and tested in a high speed rig at design point and off-design conditions. The turbine met or exceeded the expected performance level based on both steady state and radial/circumferential traverse data. High frequency dynamic total pressure measurements were made to understand the presence of unsteadiness that persists in the exhaust of a transonic turbine.

The Application of Fiber Optic Test Technology in Deformation Monitoring of Highway Corrugated Steel Pipe Culvert

2011 ◽  
Vol 255-260 ◽  
pp. 1007-1011
Author(s):  
Fan Zhang ◽  
Ping Fang ◽  
Hai Tao Qian
Keyword(s):  
Term Structure ◽  
Fiber Optic ◽  
Steel Structure ◽  
Deformation Monitoring ◽  
Steel Pipe ◽  
Test Results ◽  
Test Technology ◽  
Testing Technology ◽  
Fbg Sensors ◽  
Test Points

Compared to the traditional testing technology, the fiber bragg grating(FBG) test technology has many unique advantages and is suitable for the long-term structure health monitoring. By testing the stress and strain conditions of the corrugated steel pipe culverts under different fill heights with FBG sensors set in the inner and outer of the culverts, the mechanical properties of the steel pipe culverts could be obtained. The field fiber optic test results show that the FBG sensors can be used in the structures under complex engineering conditions. When the fill height is added, the FBG test results will change significantly in real-time, and the strain values of all test points on the culvert will change with the increase of the fill height, particularly in the top and bottom test points of the culvert. So the Fiber optic test technology can adapt to the testing requirements of the corrugated steel structure, and can provide a basis for the design of the corrugated steel pipe.

Test and Analysis of Machine Center's Principal Spindle Dynamic Errors

2013 ◽  
Vol 364 ◽  
pp. 163-166 ◽  
Author(s):  
Kuo Liu ◽  
Chun Shi Liu ◽  
Zhi Tan ◽  
Shuai Zhou
Keyword(s):  
Test Results ◽  
Machine Center ◽  
Rotating Speed ◽  
Dynamic Errors ◽  
Machine Centers ◽  
Radial Average ◽  
Radial Separation

The form of principal spindle's dynamic errors is analysed firstly. Principal spindle's radial average errors and asynchronous errors, axial average errors and asynchronous errors, minimum radial separation center of some vertical machine center are all tested with SPN-300 of API. Three vertical machine centers are tested and every machine center is tested three times at different rotating speed. The test results and the influences of all errors are analysed at last.

scholarly journals Reconstructing Compressor Non-uniform Circumferential Flow Field from Spatially Undersampled Data - Part 1: Methodology and Sensitivity Analysis

2021 ◽  
pp. 1-12
Author(s):  
Fangyuan Lou ◽  
Nicole L. Key
Keyword(s):  
Sensitivity Analysis ◽  
Flow Field ◽  
Total Pressure ◽  
Pressure Field ◽  
Sampled Data ◽  
Wavelet Approximation ◽  
Multi Stage ◽  
Reconstructed Signal ◽  
Data Points ◽  
Aero Engines

Abstract The flow field in a compressor is circumferentially non-uniform due to the wakes from upstream stators, the potential field from both upstream and downstream stators, and blade row interactions. This non-uniform flow impacts stage performance as well as blade forced vibrations. Historically, experimental characterization of the circumferential flow variation is achieved by circumferentially traversing either a probe or the stator rows. This involves the design of complex traverse mechanisms and can be costly. To address this challenge, a novel method is proposed to reconstruct compressor nonuniform circumferential flow field using spatially under-sampled data points from a few probes at fixed circumferential locations. The paper is organized into two parts. In the present part of the paper, details of the multi-wavelet approximation for the reconstruction of circumferential flow and use of the Particle Swarm Optimization algorithm for selection of probe positions are presented. Validation of the method is performed using the total pressure field in a multi-stage compressor representative of small core compressors in aero engines. The circumferential total pressure field is reconstructed from 8 spatially distributed data points using a triple-wavelet approximation method. Results show good agreement between the reconstructed and the true total pressure fields. Also, a sensitivity analysis of the method is conducted to investigate the influence of probe spacing on the errors in the reconstructed signal.

Numerical Investigation of Static and Dynamic Aerodynamic Characteristics for a Guided Projectile with Fin Slot

2014 ◽  
Vol 998-999 ◽  
pp. 442-445
Author(s):  
Hua Dong Sun ◽  
Jian Qiao Yu ◽  
Yue Song Mei ◽  
Chong Liang
Keyword(s):  
Pressure Field ◽  
Fluid Dynamic ◽  
Wind Tunnel Test ◽  
Aerodynamic Characteristics ◽  
Theoretical Research ◽  
Shape Design ◽  
Test Results ◽  
Pitch Moment ◽  
The Mean ◽  
Good Agreement

The flow field of a cruciform finned guided projectile with and without fin slot was simulated by the mean of CFD(computational fluid dynamic) numerical method. The characteristics of pressure field distribution without and different widths slots were calculated and compared. The influence of fin slot to the aerodynamic characteristics such as drag, lift, roll moment, pitch moment static aerodynamic characteristics as well as pitch, roll damping moment dynamic aerodynamic characteristics were emphasized in different angle of attack. The numerical results were certified by the good agreement between the wind tunnel test results. Important reference was provided to theoretical research and engineering for guided projectile shape design.

Aerothermodynamic Performance of a Variable Nozzle Power Turbine Stage for an Automotive Gas Turbine

1977 ◽  
Vol 99 (4) ◽  
pp. 587-592 ◽  
Author(s):  
E. H. Razinsky ◽  
W. R. Kuziak
Keyword(s):  
Total Pressure ◽  
Test Results ◽  
Turbine Stage ◽  
Positive Power ◽  
Idle Speed ◽  
Percentage Points ◽  
Pressure Profiles ◽  
Power Turbine ◽  
Performance Penalty ◽  
Power Measurements

Test results are presented for the GT-225 variable-nozzle power turbine with nozzles set at reduced, design, and increased areas and in the braking position. Comparisons are made between predicted and experimental results. At a given speed and output power, the turbine is more efficient at the design nozzle area than when area is reduced. It is shown, however, that the GT-225 engine exhibits improved part-load specific fuel consumption due to the ability to run at higher gasifier turbine inlet temperatures afforded by the variable nozzle power turbine. With the nozzles in the braking position and the gasifier turbine at idle speed, peak engine braking power is 27 percent of the maximum positive power. Measurements at the turbine discharge show that total pressure profiles are dependent on nozzle area. There is a performance penalty associated with the vane-end clearance required for movement of the variable nozzles. Tests conducted with the nozzles in the design position and with their vane-ends sealed yielded efficiency improvements of 0.7–4.0 percentage points.

The Choking Pressure Ratio of a Critical Flow Venturi

1975 ◽  
Vol 97 (4) ◽  
pp. 1251-1256 ◽  
Author(s):  
H. S. Hillbrath ◽  
W. P. Dill ◽  
W. A. Wacker
Keyword(s):  
Total Pressure ◽  
Gas Flow ◽  
Pressure Ratio ◽  
Critical Flow ◽  
Test Results ◽  
Flow Conditions ◽  
Pressure Losses ◽  
And Control ◽  
Measurement And Control ◽  
Effectiveness Parameter

The critical flow venturi has many important applications in the measurement and control of gas flow. In many of these applications, it is desirable to minimize the pressure loss required to maintain critical flow conditions. The performance of the venturi may be characterized by the ratio of outlet static pressure to inlet total pressure just sufficiently small to produce critical flow. This ratio is called choking pressure ratio (CPR). The optimization of diffusers for critical flow Venturis is discussed and suggestions for designs practice are presented. Test results are given for six different diffuser configurations, and a comparison is made with data on 11 configurations from other investigators. This work was done under contract to the National Aeronautics and Space Administration—Marshall Space Flight Center. It is shown that, for the small divergence angles considered, a simply defined diffuser effectiveness parameter is approximately independent of flow conditions and may be used to predict choking pressure ratio. Even very short diffusers greatly improve performance, and, for longer diffusers, critical flow can be maintained at total pressure losses of 5 percent.

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