Modelling for control of a jet engine compressor variable stator vanes hydraulic actuator

2016 ◽  
Author(s):  
Tomas Puller ◽  
Andrea Lecchini-Visintini
Keyword(s):  
Hydraulic Actuator ◽  
Jet Engine ◽  
Engine Compressor ◽  
Variable Stator

Remanufacture of Jet Engine Compressor Components

1973 ◽  
Author(s):  
Martin Weinstein
Keyword(s):  
Magnetic Particle ◽  
Electron Beam Welding ◽  
Diffusion Coating ◽  
Ultrasonic Inspection ◽  
Jet Engine ◽  
Turbine Engine ◽  
Gas Plasma ◽  
Engine Compressor ◽  
Compressor Performance ◽  
And Diffusion

A description of the various mechanical operations employed in the remanufacture of gas turbine engine compressor components such as blading, rotor disks and spacer, vane shroud assemblies and air seals are given. The operations described include tungsten inert gas, plasma needle arc and electron beam welding, furnace and torch brazing, glass bead and shot peening, magnetic particle and ultrasonic inspection, plasma spray and diffusion coating. Emphasis is given to the effect of these operations on the mechanical integrity of the engine component. For example, the effect of welding, brazing, peening and diffusion coating on the high cycle fatigue strength of compressor stator and rotor components is discussed. The effect of repair operations on jet engine compressor performance is also considered.

Design of One-Piece Jet-Engine Compressor End Seals

1968 ◽  
Vol 90 (4) ◽  
pp. 709-721
Author(s):  
L. W. Winn ◽  
R. L. Thorkildsen ◽  
D. F. Wilcock
Keyword(s):  
Design Procedure ◽  
Labyrinth Seals ◽  
Jet Engine ◽  
Supersonic Transport ◽  
Face Type ◽  
High Pressure Compressor ◽  
Order Of Magnitude ◽  
Engine Compressor ◽  
Gas Bearing

Performance of advanced air-breathing propulsion systems can be significantly improved through the utilization of effective sealing devices. One of the areas in which immediate benefits are realizable from improvements in sealing efficiency is the high-pressure compressor end area. This paper describes the design of a face-type flexible seal and a face-type rigid seal for a compressor end seal based upon the cruise conditions expected in one version of the supersonic transport (SST) jet engine. The seals, non-contacting during operation, operate on air films achieved through the employment of hybrid gas-bearing geometries on the seal faces. The design procedure discussed consists primarily of the selection of the most applicable seal-face geometries force and moment balance, determination of seal tracking capability, establishment of leakage characteristics, thermal gradients, and stress and deflection calculations. The design results indicate that satisfactory seal performance can be obtained with either of the two configurations. Leakage reductions of an order of magnitude compared to that encountered with labyrinth seals commonly used in existing jet-engine systems can be achieved.

AISI No. 634

Alloy Digest ◽  
1967 ◽  
Vol 16 (1) ◽  
Keyword(s):  
Stainless Steel ◽  
Corrosion Resistance ◽  
Shear Strength ◽  
Physical Properties ◽  
Precipitation Hardening ◽  
Heat Treating ◽  
Pressure Vessels ◽  
Jet Engine ◽  
Steel Mills ◽  
Engine Compressor

Abstract AISI No. 634 is a transformation and precipitation hardening stainless steel. It is used for applications such as pressure vessels, aircraft constructural components and jet engine compressor components. This datasheet provides information on composition, physical properties, hardness, elasticity, tensile properties, and shear strength as well as creep. It also includes information on corrosion resistance as well as forming, heat treating, machining, joining, and surface treatment. Filing Code: SS-190. Producer or source: Stainless steel mills.

Variable Cycle Powerplants for a Mach 2.7 Supersonic Civil Transport

1996 ◽  
Author(s):  
Louay Aleid ◽  
Pericles Pilidis
Keyword(s):  
Fuel Consumption ◽  
Preliminary Analysis ◽  
Point Of View ◽  
Variable Geometry ◽  
Jet Engine ◽  
Preliminary Results ◽  
Variable Stator ◽  
Size Variable

The aim of the work outlined in this paper is to compare three different variable cycle jet engine concepts for future SSTs. These engines are: the Turbofan-Turbojet, the Mid-Tandem Fan engine and the Double Bypass Engine. The comparison is carried out on a basis of performance, handling and sizing issues. This preliminary analysis compares S.F.C., size, variable geometry and cycle changes, and the effect of variable stator on the running lines of each compressor for each engine. The fuel bill, for two standard missions, is estimated as well. These preliminary results indicate that the three engines are quite similar in terms of general suitability. The Mid Tandem Fan appears to be an attractive proposition from the point of view of sizing, however this comes with a small penalty in fuel consumption.

Constrained Sparse Estimation for Improved Fault Isolation

2011 ◽  
Vol 133 (12) ◽  
Author(s):  
S. Borguet ◽  
O. Léonard
Keyword(s):  
Fault Isolation ◽  
Straightforward Manner ◽  
Present Contribution ◽  
Sparse Estimation ◽  
Jet Engine ◽  
High Pressure Compressor ◽  
Two Component ◽  
Variable Stator ◽  
Pressure Compressor ◽  
Health Parameters

Least-squares-based methods are very popular in the jet engine community for health monitoring purpose. Their isolation capability can be improved by using a prior knowledge on the health parameters that better matches the expected pattern of the solution i.e., a sparse one as accidental faults impact at most one or two component(s) simultaneously. On the other hand, complimentary information about the feasible values of the health parameters can be derived in the form of constraints. The present contribution investigates the effect of the addition of such constraints on the performance of the sparse estimation tool. Due to its quadratic programming formulation, the constraints are integrated in a straightforward manner. Results obtained on a variety of fault conditions simulated with a commercial turbofan model show that the inclusion of constraints further enhance the isolation capability of the sparse estimator. In particular, the constraints help resolve a confusion issue between high pressure compressor and variable stator vanes faults.

J-47 JET ENGINE COMPRESSOR FAILURES

1952 ◽  
Author(s):  
DIRECTORATE OF AEROSPACE SAFETY NORTON AFB CA
Keyword(s):  
Jet Engine ◽  
Engine Compressor

A Fluidic Compressor Bleed Control

1969 ◽  
Author(s):  
J. M. Eastman
Keyword(s):  
Pressure Ratio ◽  
Ratio Schedule ◽  
Test Results ◽  
Opening Pressure ◽  
Jet Engine ◽  
Satisfactory Performance ◽  
Wide Range ◽  
Engine Compressor

An experimental compressor air powered fluidic jet engine compressor bleed control is described and test results are shown. The control must close the bleed valves at scheduled pressure ratios, provide a reset for the opening pressure ratio schedule, and an override for fast engine deceleration. It must operate over a wide range of pressures, pressure ratios and temperatures. Satisfactory performance is indicated at all conditions.

scholarly journals A simplified model of a fueldraulic actuation system with application to load estimation

2018 ◽  
Vol 233 (5) ◽  
pp. 570-581
Author(s):  
Tomas Puller ◽  
Andrea Lecchini-Visintini
Keyword(s):  
Simplified Model ◽  
Internal Cooling ◽  
Load Estimation ◽  
Jet Engine ◽  
Input Nonlinearity ◽  
Cooling Flow ◽  
Actuation System ◽  
Mechanical Unit ◽  
Stator Vane ◽  
Variable Stator

In this work, a simplified model of the compressor variable stator vane fueldraulic actuation system of a jet engine is presented. The actuation system is a sub-assembly of the engine’s hydro-mechanical unit. A unique characteristic of the actuator is an internal cooling flow which prevents the overheating of fuel. It is shown that the effect of the cooling flow is well represented by a static input nonlinearity. The resulting model is of the Hammerstein structure. It is then shown that the model can be used for the estimation of the actuator’s external load. The results are validated using an accurate real system simulator.

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