scholarly journals Advanced Gas Turbine Concept, Design and Evaluation Methodology. Preliminary Design of Highly Loaded Low Pressure Gas Turbine of Aircraft Engine

2008 ◽  
Vol 2 (1) ◽  
pp. 17-23
Author(s):  
Leonid Romanenko ◽  
Leonid Moroz ◽  
Petr Pagur ◽  
Yuri Govoruschenko ◽  
Ennio Spano ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Aircraft Engine ◽  
Low Pressure ◽  
Evaluation Methodology ◽  
Preliminary Design ◽  
Concept Design ◽  
Highly Loaded

Comparison of Piston Concept Design Solutions for Composite Cycle Engines Part II: Design Considerations

2021 ◽  
Author(s):  
Dimitrios Chatzianagnostou ◽  
Stephan Staudacher
Keyword(s):  
Gas Turbine ◽  
Design Space ◽  
Piston Compressor ◽  
Design System ◽  
Surface Load ◽  
Preliminary Design ◽  
Concept Design ◽  
Piston Engine ◽  
Engine Design ◽  
Cylinder Piston

Abstract Hecto pressure composite cycle engines with piston engines and piston compressors are potential alternatives to advanced gas turbine engines. The nondimensional groups limiting their design have been introduced and generally discussed in Part I [1]. Further discussion shows, that the ratio of effective power to piston surface characterizes the piston thermal surface load capability. The piston design and the piston cooling technology level limit its range of values. Reynolds number and the required ratio of advective to diffusive material transport limit the stroke-to-bore ratio. Torsional frequency sets a limit to crankshaft length and hence cylinder number. A rule based preliminary design system for composite cycle engines is presented. Its piston engine design part is validated against data of existing piston engines. It is used to explore the design space of piston components. The piston engine design space is limited by mechanical feasibility and the crankshaft overlap resulting in a minimum stroke-to-bore ratio. An empirical limitation on stroke-to-bore ratio is based on existing piston engine designs. It limits the design space further. Piston compressor design does not limit the piston engine design but is strongly linked to it. The preliminary design system is applied to a composite cycle engines of 22MW take-off shaft power, flying a 1000km mission. It features three 12-cylinder piston engines and three 20-cylinder piston compressors. Its specific fuel consumption and mission fuel burn are compared to an intercooled gas turbine with pressure gain combustion of similar technology readiness.

Design of Nozzle-Less Radial Inflow Gas Turbine for Small Capacity (20 kW) Gas Turbine Engine

2004 ◽  
Author(s):  
Chetan S. Mistry ◽  
S. A. Channiwala
Keyword(s):  
Mach Number ◽  
Gas Turbine ◽  
High Speed ◽  
Velocity Ratio ◽  
Aircraft Engine ◽  
Basic Program ◽  
Specific Power ◽  
Preliminary Design ◽  
Power Requirement ◽  
Compact Size

In recent years, looking to the advantages of radial inflow gas turbine much research is focused in this area. The various applications like auxiliary drives in aircraft engine and automobile application where very high speed, compact size and greater specific power are the prime requirements, radial inflow is there by choice. The present work for the design of nozzle-less radial inflow turbine begins with power requirement of 20 kW, the parameters like temperature; pressure and mass flow rate required for the design are obtained from the detailed gas turbine cycle analysis. Based on the available data from cycle analysis initially preliminary design of rotor was developed, from the available loss models the efficiency of the turbine was found. The preliminary design provides the leading dimensions of the rotor with inlet and exit conditions. The objective of most designs will be to maximize the efficiency and/or to develop the compact size. After completion of the preliminary design of turbine, it was felt necessary to optimized the result for best efficiency accordingly an analytical study was undertaken to study the influence of different parameters like inlet absolute Mach number, relative exit Mach number, solidity, relative velocity ratio and hub to shroud radius ratio on efficiency. VISUAL BASIC program is developed to study the effect of different parameters on efficiency. From the detailed loss analysis the selection of these parameters can be made to achieve optimum performance. It is believed that present work will provide necessary guidelines for the optimal design of radial inflow gas turbine.

A Modern Approach to Conceptual/Preliminary Design of Gas Turbine Based Propulsion Systems

1994 ◽  
Author(s):  
Kamran Eftekhari Shahroudi
Keyword(s):  
Real Time ◽  
Gas Turbine ◽  
High Speed ◽  
Aircraft Design ◽  
Aircraft Engine ◽  
Graphic User Interface ◽  
Preliminary Design ◽  
Modern Approach ◽  
Design Cycle ◽  
Human Designer

This paper describes the development and implementation of the Natural Design Cycle to Conceptual/Preliminary Design of gas-turbine-based aircraft engines. The Natural Design Cycle is a high speed design optimization cycle within which the human designer is actively employed. The CAGEDR (Computer Aided General Engine Design) was developed at Delft TU to closely mimic the Natural Design Cycle. The main objective of this exercise was to obtain a modern and efficient tool to assist engineers in the conceptual/preliminary phase of gas turbine based aircraft engine mechanical and thermodynamic design, by automating many of the laborious tasks involved while leaving all intuitive and decision making tasks to the human designer. The topics discussed herein will be of interest to other propulsion software and/or CAD developers, Among them, • The Natural Design Cycle and its advantages • generation High Speed (or Real Time) Engine Models in the form of ANSI C Source Code • Integration with Aircraft Design/Analysis • Real Time Movement Through Design Space for “Human in the Loop” optimization (the Dyn-Carp and the Dyn-Hist modules) • The role of Graphic User Interface for defining engine models

scholarly journals Design and Test of the FT8 Gas Turbine Low Pressure Compressor

1989 ◽  
Author(s):  
R. J. Monhardt ◽  
J. H. Richardson ◽  
J. M. Boettcher
Keyword(s):  
Gas Turbine ◽  
Aircraft Engine ◽  
Low Pressure ◽  
Test Results ◽  
Gas Generator ◽  
Test Program ◽  
Stall Margin ◽  
Turbine Design ◽  
Pressure Compressor ◽  
Actual Test

This paper presents a discussion of the design and test phases of the Low Pressure Compressor (LPC) used in the FT8 Gas Turbine. Design objectives, including efficiency, durability and stall margin goals are covered along with actual test results indicating successful accomplishment of these objectives. Unique features of the test program and an overview of the FT8 Gas Generator in comparison to the JT8D Aircraft Engine are also presented.

Design and Testing of the FT8 Gas Turbine Low-Pressure Compressor

1990 ◽  
Vol 112 (2) ◽  
pp. 159-164
Author(s):  
R. J. Monhardt ◽  
J. H. Richardson ◽  
J. M. Boettcher
Keyword(s):  
Gas Turbine ◽  
Aircraft Engine ◽  
Low Pressure ◽  
Test Results ◽  
Gas Generator ◽  
Test Program ◽  
Stall Margin ◽  
Turbine Design ◽  
Design And Testing ◽  
Pressure Compressor

This paper presents a discussion of the design and test phases of the Low-Pressure Compressor (LPC) used in the FT8 Gas Turbine. Design objectives, including efficiency, durability, and stall margin goals, are covered along with actual test results indicating successful accomplishment of these objectives. Unique features of the test program and an overview of the FT8 Gas Generator in comparison to the JT8D Aircraft Engine are also presented.

The Effect of Pulsed Blowing on the Boundary Layer of a Highly Loaded Low Pressure Turbine Blade

2013 ◽  
Author(s):  
Marion Mack ◽  
Roland Brachmanski ◽  
Reinhard Niehuis
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Mach Number ◽  
Suction Side ◽  
Reynolds Numbers ◽  
Low Pressure ◽  
Trailing Edge ◽  
Low Pressure Turbine ◽  
Wide Range ◽  
Highly Loaded

The performance of the low pressure turbine (LPT) can vary appreciably, because this component operates under a wide range of Reynolds numbers. At higher Reynolds numbers, mid and aft loaded profiles have the advantage that transition of suction side boundary layer happens further downstream than at front loaded profiles, resulting in lower profile loss. At lower Reynolds numbers, aft loading of the blade can mean that if a suction side separation exists, it may remain open up to the trailing edge. This is especially the case when blade lift is increased via increased pitch to chord ratio. There is a trend in research towards exploring the effect of coupling boundary layer control with highly loaded turbine blades, in order to maximize performance over the full relevant Reynolds number range. In an earlier work, pulsed blowing with fluidic oscillators was shown to be effective in reducing the extent of the separated flow region and to significantly decrease the profile losses caused by separation over a wide range of Reynolds numbers. These experiments were carried out in the High-Speed Cascade Wind Tunnel of the German Federal Armed Forces University Munich, Germany, which allows to capture the effects of pulsed blowing at engine relevant conditions. The assumed control mechanism was the triggering of boundary layer transition by excitation of the Tollmien-Schlichting waves. The current work aims to gain further insight into the effects of pulsed blowing. It investigates the effect of a highly efficient configuration of pulsed blowing at a frequency of 9.5 kHz on the boundary layer at a Reynolds number of 70000 and exit Mach number of 0.6. The boundary layer profiles were measured at five positions between peak Mach number and the trailing edge with hot wire anemometry and pneumatic probes. Experiments were conducted with and without actuation under steady as well as periodically unsteady inflow conditions. The results show the development of the boundary layer and its interaction with incoming wakes. It is shown that pulsed blowing accelerates transition over the separation bubble and drastically reduces the boundary layer thickness.

Highly Loaded Low-Pressure Turbine: Design, Numerical, and Experimental Analysis

2010 ◽  
Author(s):  
J. T. Schmitz ◽  
S. C. Morris ◽  
R. Ma ◽  
T. C. Corke ◽  
J. P. Clark ◽  
...  
Keyword(s):  
High Speed ◽  
Numerical Solutions ◽  
Pressure Ratio ◽  
Low Pressure ◽  
Boundary Layer Transition ◽  
Layer Transition ◽  
Free Stream Turbulence ◽  
Low Pressure Turbine ◽  
The Mean ◽  
Highly Loaded

The performance and detailed flow physics of a highly loaded, transonic, low-pressure turbine stage has been investigated numerically and experimentally. The mean rotor Zweifel coefficient was 1.35, with dh/U2 = 2.8, and a total pressure ratio of 1.75. The aerodynamic design was based on recent developments in boundary layer transition modeling. Steady and unsteady numerical solutions were used to design the blade geometry as well as to predict the design and off-design performance. Measurements were acquired in a recently developed, high-speed, rotating turbine facility. The nozzle-vane only and full stage characteristics were measured with varied mass flow, Reynolds number, and free-stream turbulence. The efficiency calculated from torque at the design speed and pressure ratio of the turbine was found to be 90.6%. This compared favorably to the mean line target value of 90.5%. This paper will describe the measurements and numerical solutions in detail for both design and off-design conditions.

Characterization of gas turbine ingested sand particles based on electrostatic signal

2021 ◽  
pp. 095765092110464
Author(s):  
Jianzhong Sun ◽  
Heng Jiang ◽  
Caiqiong Yang ◽  
Ruochen Liu
Keyword(s):  
Theoretical Analysis ◽  
Gas Turbine ◽  
Simulation Study ◽  
Aircraft Engine ◽  
In Situ Monitoring ◽  
Service Reliability ◽  
Fem Modeling ◽  
Initial Development ◽  
Sand Particles ◽  
Particle Ingestion

Particle ingestion into a gas turbine can have serious effects on both performance and engine in-service reliability. Thus there exists a need for in situ monitoring and characterizing particulate matter entering an aircraft engine inlet for the purposes of engine damages estimation and prognosis. This paper presents the initial development of Ingested Debris Monitoring System (IDMS) signal processing method of characterizing the ingested particles. A theoretical analysis and simulation study were carried out to study the relationships between the characteristics of the ingested sand particles and the features of the IDMS signal both in frequency- and time-domain. A Finite-Element Modeling (FEM) for the IDMS Sensor was developed, then the validated FEM modeling was used for simulation experiments of particles ingestion under various conditions of different particle moving speeds, concentrations and charge-to-mass ratios. Results of the theoretical analysis and simulation study demonstrates the feasibility and effectiveness of the proposed method to provide real time information characterizing the size and concentration of ingested sand particles, and will serve as an impetus to carry out further research.

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