Development of Unshrouded Blade for Stage Two of GTE-65.1 Turbine

The development of domestic gas turbine units designed for driving electric generators or mechanical equipment at gas-pumping stations has become a crucial technological area for the power industry. At present AO Power Machines is developing the GTE-65.1 gas turbine unit (GTU), whose prototype is th...

Full description

Saved in:
Bibliographic Details
Published in:Thermal engineering 2023-07, Vol.70 (7), p.517-522
Main Authors: Granovskiy, A. V., Afanasiev, I. V., Kostege, V. K., Fokin, N. I., Cherkasova, M. G.
Format: Article
Language:English
Subjects:
Air masses
Boundary conditions
Combined-Cycle Power Plants
Electric generators
Engineering
Engineering Thermodynamics
Gas turbines
Gas-Turbine
Heat and Mass Transfer
Mass flow
Pumping stations
Reconditioning
Rotor blades
Rotor blades (turbomachinery)
Steam-Turbine
Stresses
Their Auxiliary Equipment
Turbines
Citations: Items that this one cites
Online Access:Get full text
Tags: Add Tag
No Tags, Be the first to tag this record!
Description
Summary:The development of domestic gas turbine units designed for driving electric generators or mechanical equipment at gas-pumping stations has become a crucial technological area for the power industry. At present AO Power Machines is developing the GTE-65.1 gas turbine unit (GTU), whose prototype is the GTE-65.0 GTU designed in the early 2000s. The boundary conditions adopted in designing the flow path in the modified GTE-65.1 were the shapes of the meridional outline and of the blade rows in the GTE-65.0 turbine and the main parameters under the rated operating conditions. The possibility of creating a stage two unshrouded blade for the modified GTE-65.1 turbine is examined. This solution will reduce the cooling air mass flow, decrease the cooling losses and aerodynamic losses in the tip area, and eliminate problems of bringing the strength of the cooled shroud and of the blade proper to the required level by reducing stresses in the blade body and contour stresses in the rotor disk. The operating (service) costs in this case are the comparative costs for the restoration (reconditioning) of the blade with or without a cooled shroud to be incurred after the first interval of the operating cycle corresponding to approximately 25 000–33 000 equivalent gas hours. The results of computational studies performed by the 3D NS and Fluent software packages have demonstrated that an efficient rotor blade for stage two of the GTE-65.1 GTU can be designed without any shroud.
ISSN:0040-6015
1555-6301
DOI:10.1134/S0040601523070029