Active Combustion Control for a Low-Emissions Aircraft Engine Combustor Prototype: Experimental Results

2013 ◽  
Vol 29 (4) ◽  
pp. 991-1000 ◽  
Author(s):  
John C. DeLaat ◽  
George Kopasakis ◽  
Joseph R. Saus ◽  
Clarence T. Chang ◽  
Changlie Wey
Keyword(s):  
Aircraft Engine ◽  
Experimental Results ◽  
Combustion Control ◽  
Active Combustion Control

Perspectives on linear compensator designs for active combustion control

1999 ◽  
Author(s):  
William Saunders ◽  
Michael Vaudrey ◽  
Bryan Eisenhower ◽  
Uri Vandsburger ◽  
Christopher Fannin
Keyword(s):  
Combustion Control ◽  
Active Combustion Control

The effect analysis of an engine jet on an aircraft blast deflector

2018 ◽  
Vol 41 (4) ◽  
pp. 990-1001
Author(s):  
Song Ma ◽  
Jianguo Tan ◽  
Xiankai Li ◽  
Jiang Hao
Keyword(s):  
High Temperature ◽  
Flow Field ◽  
High Speed ◽  
Deflection Angle ◽  
Stokes Equations ◽  
Three Dimensional ◽  
Aircraft Engine ◽  
Experimental Results ◽  
Exhaust Gases ◽  
The Impact

This paper establishes a novel mathematical model for computing the plume flow field of a carrier-based aircraft engine. Its objective is to study the impact of jet exhaust gases with high temperature, high speed and high pressure on the jet blast deflector. The working condition of the nozzle of a fully powered on engine is first determined. The flow field of the exhaust jet is then numerically simulated at different deflection angle using the three-dimensional Reynolds averaged Navier–Stokes equations and the standard [Formula: see text]-[Formula: see text] turbulence method. Moreover, infra-red temperature tests are further carried out to test the temperature field when the jet blast deflector is at the [Formula: see text] deflection angle. The comparison between the simulation results and the experimental results show that the proposed computation model can perfectly describe the system. There is only 8–10% variation between them. A good verification is achieved. Moreover, the experimental results show that the jet blast deflector plays an outstanding role in driving the high-temperature exhaust gases. It is found that [Formula: see text] may be the best deflection angle to protect the deck and the surrounding equipment effectively. These data results provide a valuable basis for the design and layout optimization of the jet blast deflector and deck.

Friction Damping of Interlocked Vane Segments: Experimental Results

2001 ◽  
Author(s):  
T. Berruti ◽  
S. Filippi ◽  
M. M. Gola ◽  
S. Salvano
Keyword(s):  
Numerical Analysis ◽  
Energy Dissipation ◽  
Contact Surface ◽  
Aircraft Engine ◽  
Experimental Methods ◽  
Experimental Results ◽  
Contact Model ◽  
Friction Damping ◽  
Contact Surfaces ◽  
Adjacent Segments

Experimental methods and results of the stator bladed segment of an aircraft engine are presented. Investigation concern the energy dissipation due to friction between contact surfaces of adjacent segments. The influence of the force normal to the contact surface (due to interference between adjacent segments) on friction damping is shown. Moreover the experiments show the nature of friction at contact surfaces. The parameters of a contact model to be used in a numerical analysis have been identified from the experiments.

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