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Article
Influence of Incidence on Streamlines and Profile Losses of Turbine Cascades
Analysis of results of experimental investigation of turbine cascades is carried out. It is showed that the nature of the influence of negative incidences on profile losses can be determined by the streamline ...
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Article
Study of Turbine Cascades at Negative Incidence Angles
Based on the analysis of experimental data, the influence of incidence angle on the blade loading and profile loss (hereinafter referred to as loss) in flat turbine cascades of axial turbines is refined. Wide ...
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Article
The Effect of Turbine Cascade Pitch on the Incidence Losses
The results from studies of flat subsonic and transonic cascades with the convergence ratio Cr = 1.2–3.1 are considered. Series with three to four cascades in each with the same airfoil profile and different rela...
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Article
Calculating Incidence Losses in the Turbine Cascade
The flow in turbine cascades with incidences is accompanied by a separated flow around the airfoils, which is difficult to calculate with acceptable accuracy. Therefore, in practice, empirical formulas are use...
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Article
Aerodynamic Investigation of the Turbine Vane Row with a Flared Flow Path
The influence of a bilateral flare of the flow path of the turbine nozzle vane on the flow pattern and energy losses was investigated, a search was made for ways to improve the aerodynamic performance of a suc...
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Article
Influence of the Airfoil Leading Edge Thickness on Turbine Cascade Losses Due to the Incidence
On the basis of experimental studies, it is established that the thickening of the airfoil leading edge at positive incidences increases the im**ement resistance of the moderate convergence cascade, but it d...
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Article
Investigation of Nozzle Cascades of a Turbine Stage
Two different nozzle cascades designed for an LP aircraft turbine have been investigated. The cascade had large convergence, a moderate curvature of the airfoils, and it flowed over so that the outlet subsonic...
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Article
Calculation of gas turbine characteristic
The reasons and regularities of vapor flow and turbine parameter variation depending on the total pressure drop rate π* and rotor rotation frequency n are studied, as exemplified by a two-stage compressor turbine...
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Article
Computation of the throat area of a turbine blade ring
The throat area is a geometric parameter of the blade ring necessary to profile its blades and compute the turbine capacity. As applied to the filament flow model, the area is defined by the involute of the th...
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Article
Improving of the aerodynamic characteristics of turbine transonic nozzle vane cascades
A detailed experimental investigation of two transonic turbine nozzle vane cascades aimed at improving their characteristics is carried out. The initial cascades had a convex suction side in the outlet area be...
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Article
Aerodynamic development and investigation of turbine transonic rotor blade cascades
An intricate nature of the pattern in which working fluid flows over transonic blade cascades generates the need for experimentally studying their characteristics in designing them. Three cascades having ident...
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Article
Aerodynamic investigation of turbine cooled vane block
The vane block (VB) has been investigated and it gives several important results related to test methods and calculation procedures. The vane block is characterized by a developed film and convective cooling s...
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Article
A technique for the gas dynamic calculation of the cooled multistage turbine performance
A technique of one-dimensional turbine performance calculation, implemented into a quick-operating computational code, is stated. Analytical relations for a flow outlet angle calculation as well as semi-empiri...
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Article
On shrouding a first stage high-temperature turbine blade
In this paper, some factors that help in shrouding a rotor blade are analyzed, namely, a decrease of the blade profile chord, partial cuts of the shroud, its controlled cooling. Also shown is a real possibilit...
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Article
The influence of a special fillet between the endwall and airfoil at the leading edge on the performance of the turbine nozzle diaphragm
It is shown from the results of experimental investigations carried out on a nozzle diaphragm’s sector that an enlarged fillet at the vane leading edge does not have an essential effect on the flow and energy ...
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Article
On correction of profiles in the peripheral sections of turbine unshrouded rotor blades
In this paper, it is shown that the conventional design calculation of turbines with a zero radial clearance results in no large errors of the flow parameter determination and an additional decrease of an angl...
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Article
Characteristics of turbine cascade with the modified leading edge of a profile
Some design and experimental data on two series of turbine cascades with the profiles having a conventional rounded edge and the modified profiles having the leading edge outline with continuously varied curva...
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Article
On choice of the blade back profile curvature in transonic turbine cascades
Some design and experimental data on three cascades with the same 12° bending angle for the primary nozzle block of a gas turbine are presented. As is seen from the investigation the most efficient at the tran...
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Article
Aerodynamic refinement of turbine cascades
Based on the experimental data, a dependence of the minimal friction losses in cascades was obtained. A turbine stage efficiency gain as a result of cascade improvement over the last three decades of the 20th ...
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Article
Improving the aerodynamic efficiency of blade profile cascade used in a cooled turbine
Good effect from using rotor blade cascades, the pressure side’s profile of which has a bend near the trailing edge at an angle of no larger than 15°, is confirmed from the results of experimental studies.
