Experimental and Computational Analysis of a High Performance Four-Stroke Motorcycle Engine Equipped with a Variable Geometry Exhaust System

2002 ◽  
Author(s):  
M. Badami ◽  
F. Millo ◽  
G. Giaffreda
Keyword(s):  
High Performance ◽  
Computational Analysis ◽  
Exhaust System ◽  
Variable Geometry ◽  
Motorcycle Engine

Experimental and Computational Analysis of a High-Performance Motorcycle Engine

1996 ◽  
Author(s):  
A. A. Boretti ◽  
G. Cantore ◽  
E. Mattarelli ◽  
F. Preziosi
Keyword(s):  
High Performance ◽  
Computational Analysis ◽  
Motorcycle Engine

INCOLOY ALLOY 864

Alloy Digest ◽  
1998 ◽  
Vol 47 (2) ◽  
Keyword(s):  
Corrosion Resistance ◽  
High Temperature ◽  
Mechanical Strength ◽  
High Performance ◽  
Exhaust System ◽  
Good Combination ◽  
Fatigue Properties ◽  
Temperature Performance ◽  
Incoloy Alloy ◽  
Oxidation And Corrosion

Abstract Incoloy Alloy 864 is a high performance alloy developed specifically for automotive exhaust system flexible couplings and other exhaust applications. The alloy has a good combination of oxidation and corrosion resistance, with good mechanical strength, stability, and fatigue properties. This datasheet provides information on composition, physical properties, and elasticity. It also includes information on high temperature performance and corrosion resistance as well as joining. Filing Code: SS-708. Producer or source: Inco Alloys International Inc.

scholarly journals High Performance Computational Analysis of Large-scale Proteome Data Sets to Assess Incremental Contribution to Coverage of the Human Genome

2013 ◽  
Vol 12 (6) ◽  
pp. 2858-2868 ◽  
Author(s):  
Nadin Neuhauser ◽  
Nagarjuna Nagaraj ◽  
Peter McHardy ◽  
Sara Zanivan ◽  
Richard Scheltema ◽  
...  
Keyword(s):  
Human Genome ◽  
High Performance ◽  
Large Scale ◽  
Computational Analysis ◽  
Data Sets

scholarly journals Optimization Aspects of an Ejector Type Hypersonic Thrust Nozzle

1992 ◽  
Author(s):  
G. Trittler ◽  
E. Eckert ◽  
M. Göing
Keyword(s):  
High Performance ◽  
Exhaust System ◽  
Vital Role ◽  
Calculation Model ◽  
Nozzle Geometry ◽  
Design Parameters ◽  
Axial Thrust ◽  
Thrust Coefficient ◽  
Wide Range ◽  
Low Performance

Hypersonic aircraft projects are highly dependant on efficient propulsion systems. High performance and integration within the airframe play a vital role in the overall concept. Particular attention must be paid to the exhaust system that is submitted to a wide range of operational requirements. An optimization of the nozzle geometry for high flight Mach numbers will lead to a low performance at the transonic flight regime. The additional use of secondary ejector air flow at transonic speeds is one option to improve the thrust behaviour of the nozzle. In the presented paper performance data of single expansion ramp ejector type nozzles are predicted using a calculation model based on a method-of-characteristics algorithm. For optimization purposes the effects of various design parameters on axial thrust coefficient and thrust vector angle are discussed. The geometric parameters investigated are the length of the lower nozzle wall and its deflection angle as well as the ejector slot location and its cross-section.

scholarly journals Turbogenerator: Part 1: Simulation

2018 ◽  
Vol 7 (3.15) ◽  
pp. 277
Author(s):  
Lev Yu. Lezhnev ◽  
Alexey P. Tatarnikov ◽  
Arсady A. Skvortsov ◽  
Igor A. Papkin ◽  
Aleksandr S. Nekrasov
Keyword(s):  
Mathematical Model ◽  
Power Generation ◽  
Comparative Analysis ◽  
Power Plants ◽  
Computational Analysis ◽  
Exhaust System ◽  
Electric Machine ◽  
Distributed Power Generation ◽  
Technical Solutions ◽  
Work Done

The article describes the process of developing a turbogenerator for power plants of small and distributed power generation. The analysis of the component base for the turbogenerator was carried out, and thereof a comparative analysis of possible technical solutions was conducted. The work considered the installation variants of a turbogenerator in the exhaust system, an electric machine of a turbogenerator, types of turbines of a generator. A mathematical model for computation of the output effective and geometric parameters of a turbogenerator was described. The results of computational analysis were presented, and the parameters of the turbogenerator being developed were selected. Based on the results of the work done the conclusions were made  

Computational Analysis of Unstart in Variable-Geometry Inlet

2021 ◽  
pp. 1-13
Author(s):  
Jonathan P. Reardon ◽  
Joseph A. Schetz ◽  
Kevin Todd Lowe
Keyword(s):  
Computational Analysis ◽  
Variable Geometry

Series Active Variable Geometry Suspension Robust Control Based on Full-Vehicle Dynamics

2019 ◽  
Vol 141 (5) ◽  
Author(s):  
Cheng Cheng ◽  
Simos A. Evangelou
Keyword(s):  
High Performance ◽  
Performance Enhancement ◽  
Ride Comfort ◽  
The Body ◽  
Control Technique ◽  
Variable Geometry ◽  
Physical Constraints ◽  
Car Model ◽  
Time Domains ◽  
Vertical Accelerations

This paper demonstrates the ride comfort and road holding performance enhancement of the new road vehicle series active variable geometry suspension (SAVGS) concept using an H∞ control technique. In contrast with the previously reported work that considered simpler quarter-car models, the present work designs and evaluates control systems using full-car dynamics thereby taking into account the coupled responses from the four independently actuated corners of the vehicle. Thus, the study utilizes a nonlinear full-car model that represents accurately the dynamics and geometry of a high performance car with the new double wishbone active suspension concept. The robust H∞ control design exploits the linearized dynamics of the nonlinear model at a trim state, and it is formulated as a disturbance rejection problem that aims to reduce the body vertical accelerations and tire deflections while guaranteeing operation inside the existing physical constraints. The proposed controller is installed on the nonlinear full-car model, and its performance is examined in the frequency and time domains for various operating maneuvers, with respect to the conventional passive suspension and the previously designed SAVGS H∞ control schemes with simpler vehicle models.

Design of a High-Performance Axial Compressor for Utility Gas Turbine

1992 ◽  
Vol 114 (2) ◽  
pp. 277-286 ◽  
Author(s):  
A. Sehra ◽  
J. Bettner ◽  
A. Cohn
Keyword(s):  
Gas Turbine ◽  
High Performance ◽  
High Efficiency ◽  
Guide Vane ◽  
Design Flow ◽  
Design Parameters ◽  
Design System ◽  
Inlet Guide Vane ◽  
Variable Geometry ◽  
Compressor Design

An aerodynamic design study to configure a high-efficiency industrial-size gas turbine compressor is presented. This study was conducted using an advanced aircraft engine compressor design system. Starting with an initial configuration based on conventional design practice, compressor design parameters were progressively optimized. To improve the efficiency potential of this design further, several advanced design concepts (such as stator ends bends and velocity controlled airfoils) were introduced. The projected poly tropic efficiency of the final advanced concept compressor design having 19 axial stages was estimated at 92.8 percent, which is 2 to 3 percent higher than the current high-efficiency aircraft turbine engine compressors. The influence of variable geometry on the flow and efficiency (at design speed) was also investigated. Operation at 77 percent design flow with inlet guide vanes and front five variable stators is predicted to increase the compressor efficiency by 6 points as compared to conventional designs having only the inlet guide vane as variable geometry.

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