Numerical modeling of the mechanism of coarse droplets deposition on surfaces of a steam turbine nozzle blade cascade

2018 ◽  
Vol 1128 ◽  
pp. 012137 ◽  
Author(s):  
V Tishchenko ◽  
R Alekseev
Keyword(s):  
Numerical Modeling ◽  
Steam Turbine ◽  
Blade Cascade ◽  
Nozzle Blade

The best angle of hot steam injection holes in the 3D steam turbine blade cascade

2022 ◽  
Vol 173 ◽  
pp. 107387
Author(s):  
Amir Kafaei ◽  
Fahime Salmani ◽  
Esmail Lakzian ◽  
Włodzimierz Wróblewski ◽  
Mikhail S. Vlaskin ◽  
...  
Keyword(s):  
Steam Turbine ◽  
Turbine Blade ◽  
Steam Injection ◽  
Blade Cascade ◽  
Steam Turbine Blade

Aerodynamic Characteristics of Steam Turbine Prismatic Blade Section

2016 ◽  
Vol 821 ◽  
pp. 48-56 ◽  
Author(s):  
Tomáš Jelínek ◽  
Petr Straka ◽  
Milan Kladrubský
Keyword(s):  
Steam Turbine ◽  
Free Stream ◽  
Numerical Approach ◽  
Operating Conditions ◽  
Bypass Transition ◽  
Inlet Flow ◽  
Flow Angle ◽  
Free Stream Turbulence ◽  
Blade Cascade ◽  
Blade Section

For the needs of high-performance steam turbines producer the data of a blade section measurement have been analyzed in detail using an experimental and numerical approach. The blade section is used on prismatic blades in high and medium pressure steam turbine parts. The linear blade cascade was tested at four pitch/chord ratios at two different stagger angles. The blade cascade was tested under two levels of Reynolds number in the range of output izentropic Mach numbers from 0.4 to 0.9.The inlet of the test section was measured pitch-wise by five-hole probe to determine the inlet flow angle. The free stream turbulence of inlet flow was determined at 2.5% what is very close to the operating conditions on first high pressure stages. Two-dimensional flow field at the center of the blades was traversed pitch-wise downstream the cascade by means of a five-hole needle pressure probe to find out the overall integral characteristics. The blade loading was measured throughout surface pressure taps at the blade center. An in-house code based on a system of Favre-averaged Navier-Stokes equation closed by non-linear two-equation EARSM k-ω turbulence model was adopted for the predictions. The code utilizes an algebraic model of bypass transition valid for both attached and separated flows taking into account the effect of free-stream turbulence and pressure gradient. Results are presented by integral characteristic in means of kinetic energy loss coefficient and velocity or pressure distribution in the blade wakes or on the blade surface. In this article, the effect of investigated criteria and comparison of experimental and numerical approach are presented and discussed.

scholarly journals Experimental study of the efficiency of steam injection on wet-steam turbine stator blade cascade

2017 ◽  
Vol 891 ◽  
pp. 012256 ◽  
Author(s):  
S.V. Khomyakov ◽  
R.A. Alexeev ◽  
I.Y. Gavrilov ◽  
V.G. Gribin ◽  
A.A. Tishchenko ◽  
...  
Keyword(s):  
Experimental Study ◽  
Steam Turbine ◽  
Steam Injection ◽  
Wet Steam ◽  
Turbine Stator ◽  
Blade Cascade ◽  
Stator Blade

Aerodynamic Performance of Nozzle Blade Cascade with Meridian-shrank Endwall Profile

2013 ◽  
Vol 13 (7) ◽  
pp. 1052-1058 ◽  
Author(s):  
Feng Zi-Ming ◽  
Zhang Jin-Dong ◽  
Gu Hui-Bin
Keyword(s):  
Aerodynamic Performance ◽  
Blade Cascade ◽  
Nozzle Blade

A comprehensive investigation of finding the best location for hot steam injection into the wet steam turbine blade cascade

Energy ◽  
2020 ◽  
Vol 190 ◽  
pp. 116397 ◽  
Author(s):  
Mohammad Ali Faghih Aliabadi ◽  
Esmail Lakzian ◽  
Iman Khazaei ◽  
Ali Jahangiri
Keyword(s):  
Steam Turbine ◽  
Turbine Blade ◽  
Steam Injection ◽  
Wet Steam ◽  
Comprehensive Investigation ◽  
Blade Cascade ◽  
Steam Turbine Blade

scholarly journals REGARDING CERTAIN AERODYNAMIC SOURCES OF NON-STATIONARY FORCE LOADS ON TURBINE PROFILES

2018 ◽  
Vol 20 ◽  
pp. 73-77
Author(s):  
Tomáš Radnic ◽  
Martin Luxa ◽  
David Šimurda
Keyword(s):  
Supersonic Flow ◽  
Flow Field ◽  
Steam Turbine ◽  
Rotor Blade ◽  
Trailing Edge ◽  
Blade Cascade ◽  
Cascade Flow ◽  
Unsteady Force ◽  
Last Stage ◽  
Large Output

The paper deals with selected phenomena present in a blade cascade flow field. The presented research was performed on prismatic blade cascades composed mostly of the tip and root sections of the last stage rotor blade of a large output steam turbine. The unstarted supersonic flow on the cascade inlet, the separation of the flow and the swirl line behind the trailing edge have been identified as the possible sources of the unsteady force effects.

Experimental Studies of Supersonic Steam Flow in the Flat Nozzle Blade Cascade at Different Initial Steam Conditions

2014 ◽  
Author(s):  
Vladimir Gribin ◽  
Aleksandr Tishchenko ◽  
Ilya Gavrilov ◽  
Victor Tishchenko ◽  
Sergey Khomyakov ◽  
...  
Keyword(s):  
Shock Waves ◽  
Visual Information ◽  
Initial Conditions ◽  
Experimental Studies ◽  
Steam Flow ◽  
Wave System ◽  
Frequency Spectra ◽  
Blade Cascade ◽  
Object Of Study ◽  
Nozzle Blade

The results of experimental studies of supersonic steam flow downstream the flat turbine nozzle blade cascade has been considered. The investigations were carried out in a broad range of steam initial conditions (superheated, dry saturated) and isentropic Mach (M1t) number downstream the object of study. The schlieren method was used to obtain the visual information about shock waves structure. The flow parameters oscillations were measured by pressure transducers situated at different locations downstream the object of study. It is shown that the occurrence of condensing shock at conditions of superheated steam upstream the nozzle blade cascade leads to the sufficient unsteadiness of shock waves system. This is due to the complex relationship between the boundary layer and a shock wave system. With changing of initial steam conditions the rearrangement of static pressure frequency spectra is observed.

The Influence of Cooling Flows on the Operating Conditions of the Ultra-Supercritical Steam Turbine Components

2010 ◽  
Author(s):  
Wojciech Kosman
Keyword(s):  
Numerical Modeling ◽  
Steam Turbine ◽  
Power Plants ◽  
Measurement Data ◽  
Test Stand ◽  
Operating Conditions ◽  
Temperature Fields ◽  
Inlet Section ◽  
Steam Turbines ◽  
Cooling Flows

This paper presents the results of the analysis on the heat transfer in the inlet section of an ultra-supercritical steam turbine. Such power generating units become the foundation of new coal-fired power plants. The monitoring of their operation is in many aspects similar to the traditional, sub-critical steam turbines. However, higher live and reheat steam parameters result in several key differences, which must be taken into the consideration when assessing the thermal and strength states of the turbines main components for the diagnostic supervision. One of the main differences is the presence of the cooling and designs specific for ultra-supercritical steam turbines, which aim to protect their components against overheating. The research described in this paper investigates the inlet section of the turbines, which is the area exposed to the highest thermal loads. The scope of the research includes both, numerical modeling and laboratory testing. A test stand has been built for the analysis of the flows in the inlet section. Cooling flows are under special attention here as their temperature field is coupled to the temperature fields of the turbine components (the rotor and the inner casing) due to the relatively small amount of the coolant. The paper provides detailed description of the test stand and some early measurement results, which involve the operation with cooling. Also the numerical modeling results are shown and compared to the measurement data.

scholarly journals Flow Characteristics of the Nozzle Blade Cascade in the Mode of the Joint Operation with the Radial Diffuser

2021 ◽  
pp. 5-11
Author(s):  
Alexander Lapuzin ◽  
Valery Subotovich ◽  
Yuriy Yudin ◽  
Svetlana Naumenko ◽  
Ivan Malymon
Keyword(s):  
Reynolds Number ◽  
Flow Rate ◽  
Rate Coefficient ◽  
Measurement Data ◽  
Flow Characteristics ◽  
Flow Coefficient ◽  
Blade Cascade ◽  
Flow Rate Coefficient ◽  
Wide Range ◽  
Nozzle Blade

The obtained research data are given for the nozzle cascade used by a small-size gas turbine of an average fanning in combination with the radial diffuser. Aerodynamic characteristics of the nozzle blade cascade were determined in a wide range of a change in the Reynolds number varying from 4∙105 to 106 and the reduced velocity varying in the range of 0.4 to 1.13. The flow rate coefficient of the nozzle cascade was derived for all modes using the integral methods and the drainages behind the cascade. The kinetic energy loss coefficient and the flow angles were calculated using the measurement data of flow parameters in three control modes that were obtained due to the use of orientable pneumometric probes. When the expansion degree of the convergent –divergent annular duct behind the cascade is equal to 1.43 the flow in the narrow section of this duct is “enlocked” in the mode when the reduced velocity behind the cascade is equal to 1.127. At such velocity the Reynolds number 106 is self-similar for the flow rate coefficient. At lower values of Reynolds number, the decrease of it is accompanied by an intensive decrease in the flow rate coefficient for all the values of the reduced velocity. For the Reynolds number lower than 7∙105 an increase in the velocity results in a decreased flow rate coefficient. When this number exceeds 8∙105 an increase in the velocity results in an increase of the flow coefficient up to the moment when the flow is “enlocked” in the nozzle cascade.

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