Mach number distribution on blade to blade surface of a turbine stator pasage

Mach number distribution on the blade to blade surface l was computed at the hub, mean and tip sections of a stator' blade using the computer program COMPBLADE. These results,; were used to plot i so-Mach contours on the blade to blade surface and surface velocity distribution as a function- of fractional surface length. The results have been presented`' in this report

Theoretical predictions of flow distribution in cascades of HP turbine blade HUB section

The stator and rotor blade hub sections designed for a\ud High pressure turbine stage were studied in detail for their\ud Aerodynamic characteristics. The profile sections were tested In the national aeronautical laboratory cascade tunnel over a Range of exit flow mach numbers. The flow field characteristics Of the cascades were analysed by the euler code based on denton"s Method. The results indicated that there is a scope for improving The blade profile sections for high mach number applications.\u

Aerodynamic and Heat Transfer Studies on HUB sections of a high pressure turbine blade: summary report

The stator and rotor blade hub sections designed for a high pressure turbine stage were studied in detail for their aerodynamic and heat transfer characteristics . The profile sections were tested in the National Aeronautical Laboratory Cascade Tunnels over a range of exit flow Mach numbers . The flow field and heat transfer characteristics of the cascades were also code based on Denton's method and the boundary layer code incorporating K- E turbulence model. The results indicated that there was a scope for improving the blade profile sections for high Mach number applications

Instrumentation for kaveri HP turbine stage test

Full scale tests are planned to be carried out on the h.p. Turbine stage of kaveri engine•''%at the turbine test rig of gas Turbine research establishment (gtre), bangalore. The instrumentation requirements for carrying out these tests were. Worked out in detail jointly by nal and gtre . The tests at gtre, turbine test rig involve the overall performance evaluation of the turbine stage and the detailed traverse measurements of flow parameters within the turbine stag . Description of the instrumentation proposed for these tests are presented in this report. The require ements of the data acquisition system has also been include

Theoretical Evaluation of H.P Turbine Blade profiel sections for GTX-35 VS Engine

High pressure turbine blade profile sections of GTX-35 VS engine were analysed by 2D-Euler code and a boundary layer code employing a (K- E) turbulence model . Computation was carried out to study velocity distribution on the profile surfaces and separation phenomenon for prescribed inlet free stream turbulence . The report presents the results of computation carried out on stator hub, mean and tip sections and rotor, hub and mean sections in detail

Turbo power pack - Phase I

A compact turbo power pack was designed for application i n underwater propulsion . The turbo power pack designed consists of a high pressure ratio supersonic partial admission impulse turbine coupled to a reduction gear box to reduce the turbine shaft speed to the level of the shaft speeds of the contrarotating propellers . The possible configurations of the turbine and gear box were studied to optimise the system and the design parameters . The report presents the details of the final configuration of the system

Relative Flow Mach Number Distribution on the Blade PD PR 8606 Profiles of a Turbine Stage

The relative flow Mach number distributions on the surface of stator and rotor blade sections of a turbine stage were determined using the, computer programme COMPBLADE at three radial stations. For the stator blade sections, iso-Mach number contours on the blade to blade surface and the flow Mach number on the blade surface as a function of blade surface length were plotted at the design flow conditions. The rotor profiles were analyzed at the reduced flow Mach numbers, because of, convergence - problem at the design conditions

Design review on the project turbo power pack Phase I

The material to be presented in the design review meeting on 20th August, 1990 at Naval Science and Technological Laboratory (NSTL), Visakhapatnam, on the project 'Turbo Power Pack - Phase I' sponsored by NSTL is compiled in this project documen

Test facility for performance evaluation of model turbine stages

The turbine test facility established at the propulsion division of NAL is suitable for carrying out performance tests on model turbine stages.Such performance tests play an important role in the development of a new turbomachine or gas turbine engine since model turbine stages could be built and tested in a short time with a relatively small investment and useful design data could be generated in the early phases of development of a new system.The paper describes the versatile test facility established at NAL for performance evaluation of model turbine stages

Turbine test facility of Propulsion Division

Development of turbine test facility in the propulsion division of NAL Bangalore was initiated in 1970.This facility is intended to carry out performance evaluation of model turbine stages and to generate stage design data which would be useful in the development of full-scale turbines.In edition,the rotating stage data would provide a measure of correlation with cascade.this report deals with the detailed description of the test facility and its capabilities