scholarly journals Small Turbine Engine Augmentor. Phase 1. Preliminary Design Studies of Afterburner and Duct-Burner Configurations

1981 ◽  
Author(s):  
T. E. Kuhn ◽  
T. W. Bruce ◽  
H. C. Mongia
Keyword(s):  
Phase 1 ◽  
Preliminary Design ◽  
Design Studies ◽  
Turbine Engine ◽  
Duct Burner

Augmenting Aerodynamic Lift with Jet Lift

1961 ◽  
Vol 65 (612) ◽  
pp. 830-832 ◽  
Author(s):  
Paul D. Arthur ◽  
Edward T. Pitkin
Keyword(s):  
System Size ◽  
The Body ◽  
Minor Effect ◽  
Preliminary Design ◽  
Propulsive Efficiency ◽  
Design Studies ◽  
Lifting Surfaces ◽  
A Minor ◽  
Propulsive Jet ◽  
Aerodynamic Lift

Downward deflection of a propulsive jet may be employed to augment aerodynamic lift in an advantageous manner. In each situation there occurs a simple optimisation when the losses due to reduced propulsive efficiency are contrasted with the gains which accrue from jet lifting. Typical cases will be considered here for wing dominant configurations, i.e. cases where the lifting surfaces contribute most of the drag, with the body contributing but a minor effect. Variable geometry of both airframe and engine is implicitly assumed so that results may be applied to preliminary design studies which will determine the relative propulsion system size and wing area.

Automated Thermal and Stress Preliminary Analyses Applied to a Turbine Rotor

2016 ◽  
Author(s):  
Maxime Moret ◽  
Alexandre Delecourt ◽  
Hany Moustapha ◽  
Francois Garnier ◽  
Acher-Igal Abenhaim
Keyword(s):  
Design Process ◽  
Turbine Rotor ◽  
Tip Clearance ◽  
Conceptual System ◽  
Preliminary Design ◽  
Design Phase ◽  
Detailed Design ◽  
Turbine Engine ◽  
Cad Models ◽  
The Impact

The use of Multidisciplinary Design Optimization (MDO) techniques at the preliminary design phase (PMDO) of a gas turbine engine allows investing more effort at the pre-detailed phase in order to prevent the selection of an unsatisfactory concept early in the design process. Considering the impact of the turbine tip clearance on an engine’s efficiency, an accurate tool to predict the tip gap is a mandatory step towards the implementation of a full PMDO system for the turbine design. Tip clearance calculation is a good candidate for PMDO technique implementation considering that it implies various analyses conducted on both the rotor and stator. As a first step to the development of such tip clearance calculator satisfying PMDO principles, the present work explores the automation feasibility of the whole analysis phase of a turbine rotor preliminary design process and the potential increase in the accuracy of results and time gains. The proposed conceptual system integrates a thermal boundary conditions automated calculator and interacts with a simplified air system generator and with several conception tools based on parameterized CAD models. Great improvements were found when comparing this work’s analysis results with regular pre-detailed level tools, as they revealed to be close to the one generated by the detailed design tools used as target. Moreover, this design process revealed to be faster than a common preliminary design phase while leading to a reduction of time spent at the detailed design phase. By requiring fewer user inputs, this system decreases the risk of human errors while entirely leaving the important decisions to the designer.

Static Analysis of Suspended Pipes

2019 ◽  
Vol 142 (1) ◽  
Author(s):  
R. P. Nordgren ◽  
C. G. Langner
Keyword(s):  
Differential Equation ◽  
Ordinary Differential Equation ◽  
Slope Angle ◽  
Elastic Rods ◽  
Preliminary Design ◽  
Order Ordinary Differential Equation ◽  
Design Studies ◽  
End Conditions ◽  
Applied Tension ◽  
Basic Equations

Abstract We analyze a suspended pipe with the application to offshore pipelaying and suspended production risers. Basic equations from the planar theory of elastic rods are reduced to a second-order ordinary differential equation with special end conditions that is solved numerically. Dimensionless results are given for the maximum curvature in the sag portion of the pipe and the slope angle at the upper end of the pipe in the absence of hydrodynamic forces. Both a rigid and a compliant seafloor are treated. We find that tension is highly effective in limiting curvature. A equation is found for the applied tension at the upper end of the pipe. Our results are intended for preliminary design studies that can be followed by more sophisticated analyses.

Lycoming T-53 Gas Turbine Engine Modification for Industrial Application

2007 ◽  
Author(s):  
Vladimir Lupandin ◽  
Martyn Hexter ◽  
Alexander Nikolayev
Keyword(s):  
Power Generation ◽  
Gas Turbine ◽  
Alternative Fuels ◽  
Phase 1 ◽  
Development Program ◽  
Gas Turbine Engine ◽  
Combustion System ◽  
Original Design ◽  
High Hydrogen ◽  
Turbine Engine

This paper describes a development program active at Magellan Aerospace Corporation since 2003, whereby specific modifications are incorporated into an Avco Lycoming T-53 helicopter gas turbine engine to enable it to function as a ground based Industrial unit for distributed power generation. The Lycoming T-53 is a very well proven and reliable two shaft gas turbine engine whose design can be traced back to the 1950s and the fact of its continued service to the present day is a tribute to the original design/development team. Phase 1 of the Program introduces abradable rotor path linings, blade coatings and changes to seal and blade tip clearances. Magellan has built a test cell to run the power generation units to full speed and full power in compliance with ISO 2314. In co-operation with Zorya-Mashproekt, Ukraine, the exhaust emissions of the existing combustion system for natural gas was reduced by 30%. New nozzles for low heat value fuels and for high hydrogen content fuels (up to 60% H2) have been developed. The T-53 gas turbine engine exhaust gas temperature is typically around 620 deg C, which makes it a very good candidate for co-generation and recuperated applications. As per Phase 2 of the program, the existing helicopter integral gearbox and separate industrial step-down gearbox will be replaced with single integral gearbox that will use the same lubrication oil system as the gas turbine engine. The engine power output will increase to 1200 kW at the generator terminals with an improvement to 25% efficiency ISO. Phase 3 of the Program will see the introduction of a new silo type combustion system, developed in order to utilize alternative fuels such as bio-diesel, biofuel (product of wood pyrolysis), land fill gases, syn gases etc. Phase 4 of the Program in cooperation with ORMA, Russia will introduce a recuperator into the package and is expected to realize a boost in overall efficiency to 37%. The results of testing the first two T-53 industrial gas turbine engines modified per Phase 1 will be presented.

Preliminary design studies of a 100 MeV H−/H+ LINAC as injector for SNS synchrotron/ADS LINAC

Pramana ◽  
2002 ◽  
Vol 59 (5) ◽  
pp. 859-869 ◽  
Author(s):  
S A Pande ◽  
Moonooku Prasad ◽  
Nita Kulkarni ◽  
P R Hannurkar
Keyword(s):  
Preliminary Design ◽  
Design Studies
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