The Influence of Flow Path Geometry and Manufacturing Tolerances on Gas Turbine Regenerator Efficiency

1974 ◽  
Author(s):  
M. Köhler
Keyword(s):  
Gas Turbine ◽  
Flow Path ◽  
Manufacturing Tolerances ◽  
Path Geometry

Acoustic Characteristics of a Gas Turbine Exhaust Model

1974 ◽  
Vol 96 (3) ◽  
pp. 181-184 ◽  
Author(s):  
J. R. Cummins
Keyword(s):  
Gas Turbine ◽  
Acoustic Radiation ◽  
Flow Path ◽  
Scale Model ◽  
Temperature Ratio ◽  
Acoustic Characteristics ◽  
Gas Turbine Exhaust ◽  
Acoustical Data ◽  
Turbine Exhaust

To investigate the sources of acoustic radiation from a gas turbine exhaust, a one-seventh scale model has been constructed. The model geometrically scales the flow path downstream of the rotating parts including support struts and turning vanes. A discussion and comparison of different kinds of aerodynamic and acoustic scaling techniques are given. The effect of the temperature ratio between model and prototype is found to be an important parameter in comparing acoustical data.

A Study on the Flowfield of an Innovative Z-Flowpath Gas Turbine Combustor

2010 ◽  
Author(s):  
Zongming Yu ◽  
Yong Huang ◽  
Fang Wang
Keyword(s):  
Gas Turbine ◽  
Reverse Flow ◽  
Flow Path ◽  
Main Flow ◽  
Wall Area ◽  
Pressure Losses ◽  
Micro Gas Turbine ◽  
Primary Zone ◽  
Commercial Code ◽  
The Stability

Reverse flow combustors were widely used in small and micro gas turbine engines. The wall area of this type of combustors was quite large. And there were two flow turning points in their flow-path. Thus the wall cooling and main flow dilution were two intrinsic problems for them. Apart from that, their high pressure losses and heavy weight were also two problems which seriously deteriorate the performance of the engines. Moreover, their primary hole jets on opposite walls were non-symmetrical, which would affect the stability and intensity of the recirculation flows. In order to improve the combustion performance, a new conceptual Z-flowpath combustor was proposed. The new combustor consisted of two 45 degree yawing instead of returning in the main flow-path. The flowfield of the new combustor was predicted by the commercial code FLUENT, after a validation for the flowfield in a model reverse flow combustor with previous experimental results. The prediction showed that the flowfield of the primary zone in the Z-flowpath combustor was highly symmetrical, the size and the intensity of the recirculation zone were about 10 and 2 times greater than the normal reverse flow combustor, respectively, while the pressure loss and the total area of the flame tube wall of the Z-flowpath combustor were decreased dramatically to be 69.4% and 51% of that in the reverse flow combustor, respectively.

Improvements to the Performance of a Prototype Pulse, Pressure-Gain, Gas Turbine Combustor

1990 ◽  
Vol 112 (1) ◽  
pp. 67-72 ◽  
Author(s):  
J. A. C. Kentfield ◽  
L. C. V. Fernandes
Keyword(s):  
Secondary Flow ◽  
Gas Turbine ◽  
Pulse Pressure ◽  
Path Length ◽  
Flow Path ◽  
Maximum Pressure ◽  
Gas Turbine Combustor ◽  
Flow Passage ◽  
Delivery Pressure ◽  
Flow Path Length

A description is given of a simple, prototype, pulse, pressure-gain combustor for a gas turbine. The work reported was targeted at alleviating problems previously observed with the prototype combustor. These were related to irreversibilities, causing a performance deficiency, in the secondary flow passage. The work consisted of investigating experimentally the effect of tuning the secondary-flow path length, adding a flow restrictor at the combining-cone entry station, and redesigning the combining cone itself. The overall result was to eradicate the previously noted performance deficiency, thereby increasing the maximum pressure gain obtained in the gas turbine from 1.6 to 4.0 percent of the compressor absolute delivery pressure.

Optimization of Controllers for Gas Turbine Based on Probabilistic Robustness

2009 ◽  
Vol 131 (5) ◽  
Author(s):  
Chuanfeng Wang ◽  
Donghai Li ◽  
Zheng Li ◽  
Xuezhi Jiang
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Controller Design ◽  
Dynamic Performance ◽  
Optimization Method ◽  
Monte Carlo Experiment ◽  
Performance Requirements ◽  
System Robustness ◽  
Manufacturing Tolerances ◽  
Probabilistic Robustness

An optimization method for controller parameters of a gas turbine based on probabilistic robustness was described in this paper. As is well known, gas turbines, like many other plants, are stochastic. The parameters of a plant model are often of some uncertainties because of errors in measurements, manufacturing tolerances and so on. According to model uncertainties, the probability of satisfaction for dynamic performance requirements was computed as the objective function of a genetic algorithm, which was used to optimize the parameters of controllers. A Monte Carlo experiment was applied to test the control system robustness. The advantage of the method is that the entire uncertainty parameter space can be considered for the controller design; the systems could satisfy the design requirements in maximal probability. Simulation results showed the effectiveness of the presented method in improving the robustness of the control systems for gas turbines.

Numerical study of the effect of flow path geometry on the property of a monopivot centrifugal blood pump

2017 ◽  
Vol 2017.29 (0) ◽  
pp. 1B12
Author(s):  
Daiki GOTO ◽  
Toru HYAKUTAKE ◽  
Masahiro NISHIDA ◽  
Daisuke SAKOTA ◽  
Ryo KOSAKA ◽  
...  
Keyword(s):  
Numerical Study ◽  
Flow Path ◽  
Blood Pump ◽  
Centrifugal Blood Pump ◽  
Path Geometry

S022011 Numerical Study of Impeller Flow Path Geometry of Circulatory Support Device with Monopivot Bearing

2013 ◽  
Vol 2013 (0) ◽  
pp. _S022011-1-_S022011-5
Author(s):  
Kento NAKAYAMA ◽  
Masahiro NISHIDA ◽  
Daisuke SAKOTA ◽  
Ryo KOSAKA ◽  
Takashi YAMANE ◽  
...  
Keyword(s):  
Numerical Study ◽  
Flow Path ◽  
Circulatory Support ◽  
Support Device ◽  
Path Geometry ◽  
Circulatory Support Device

Probabilistic Life Assessment of Turbine Vanes

2011 ◽  
Author(s):  
Alexander N. Arkhipov ◽  
Yevgeny E. Krasnovskiy ◽  
Igor V. Putchkov
Keyword(s):  
Mechanical Properties ◽  
Gas Turbine ◽  
Material Properties ◽  
Field Data ◽  
Life Assessment ◽  
Creep Life ◽  
Thermal Boundary Conditions ◽  
Life Distributions ◽  
Manufacturing Tolerances ◽  
Life Analysis

Life of a gas turbine vane generally depends on different factors such as scatter of material properties, load variation and manufacturing tolerances. However, deterministic finite element (FE) life analysis gives just a discrete value typically based on the nominal or worst case conditions. It precludes considering sensitivity to the input parameters and obtaining the expected life range. To consider the possible variations of the input parameters from their nominal values, a probabilistic approach has been applied to compute the LCF (Low Cyclic Fatigue) and creep life distributions for the uncooled vane. The deterministic 3D FE life assessment of the gas turbine components is based on the input data such as physical and mechanical properties of the base material and coating at operating temperatures, nominal geometry of the component, thermal and mechanical loadings. Each of the above mentioned inputs has its own scatter band characterized either by average and minimum values of mechanical properties (tensile strength, LCF, creep) or by variations of manufacturing tolerances; thermal boundary conditions and gas pressure distribution. The probabilistic life analysis has been performed in order to assess individual impact of each input on vane’s life scatter. LCF and creep life distributions as well as variation of the base metal oxidation layer thickness have been obtained for each scatter factor and for their overall contribution. It is seen from results that LCF and creep lives of the analyzed vane have been influenced mainly by material properties and secondarily by OTDF (hot gas temperature variation in the circumferential direction) and uncertainties of thermal boundary conditions, which depended on the operation conditions of the engine. Manufacturing tolerances and alternation of ambient air temperature in the compressor intake have the lowest impact. The derived model is useful for the risk analysis or maintenance planning. For instance, it has been shown how probability of small fatigue crack indication in one vane can be extended onto the overall probability for the failure detection of n vanes at the stator stage during regular inspection. The probability of micro crack growth due to creep after the determined amount of operating hours for the single vane may be also redefined into the overall stage probability for the detection of n such vanes. To perform validation, normalized field data have been used for comparison with the analytical predictions. Good correlations between the field data and analytical predictions have been shown.

scholarly journals МЕТОД РАСЧЁТА ТЕРМОГАЗОДИНАМИЧЕСКИХ ПАРАМЕТРОВ ТУРБОВАЛЬНОГО ГАЗОТУРБИННОГО ДВИГАТЕЛЯ НА ОСНОВЕ ПОВЕНЦОВОГО ОПИСАНИЯ ЛОПАТОЧНЫХ МАШИН. ЧАСТЬ II. ОПРЕДЕЛЕНИЕ ПАРАМЕТРОВ СТУПЕНЕЙ И МНОГОСТУПЕНЧАТЫХ КОМПРЕССОРОВ

2019 ◽  
pp. 18-28 ◽  
Author(s):  
Людмила Георгиевна Бойко ◽  
Александр Евгеньевич Демин ◽  
Наталия Владимировна Пижанкова
Keyword(s):  
Gas Turbine ◽  
Calculation Method ◽  
Axial Compressor ◽  
Flow Path ◽  
Dynamic Parameters ◽  
Operating Characteristics ◽  
Program Complex ◽  
Gas Dynamic ◽  
Multistage Compressor ◽  
Multistage Axial Compressor

Gas Turbine Engine (GTE) operating characteristics such as thrust (or power), specific fuel consumption and other cycle parameters on different regimes, can be determined by engine modeling and applying correspondent calculation method. Its accuracy is the function of the engine’s element maps definition precision. So these maps representations influence for engines investigation results significantly. Main points and equation system for engine performances calculation method were represented in Part I of this article. The method gives an opportunity for the flow path thermodynamical parameters and engine integral values analyzing by using multistage axial blade machines blade-to-blade descriptions. The compressor and gas turbine and parameters are getting by special program modules, adding to the engine operating characteristics investigation program complex. These modules use the flow path and cascade middle radius geometrical parameters as the data for calculation. The goal of this article is the representation of the method for axial stages and multistage compressors performances definition. The calculation technique is based on one-dimensional (1D) multistage axial compressor flow description. Proposed 1D flow analysis method allows to get the multistage axial compressor maps taking into account the blade-to-blade gaps flow bleeding and by-pass. The method including is founded on the thermal and gas dynamic equations and turbomachinery theoretical dependences and empirical functions for losses and deviation angles determination. Besides, the representing method allows to calculate gas dynamic parameters, velocity triangles, angles of attack, evaluate their deviations from optimal values, hydraulic losses. Also, it can show accordance of stages working on different regimes, find the stage, which is a reason for compressor instability, and stall margin. This method can be used in GTE mathematic simulation, founded on blade-to-blade description multistage blade machines or also in multistage compressor designing. The proposed method gives the opportunity to control the stator variable vanes stagger angles control and to analyze its influence for stage and multistage compressor gas dynamic parameters and maps.

scholarly journals Design concept of high-power supercritical CO2 Allam cycle gas turbine flow path

Vestnik IGEU ◽  
2018 ◽  
pp. 5-14
Author(s):  
A.N. Rogalev ◽  
◽  
E.Yu. Grigoryev ◽  
V.O. Kindra ◽  
S.K. Osipov ◽  
...  
Keyword(s):  
Gas Turbine ◽  
High Power ◽  
Supercritical Co2 ◽  
Flow Path ◽  
Design Concept ◽  
Turbine Flow Path
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