Turbine Engine Automated Trim Balancing and Vibration Diagnostics

1978 ◽  
Author(s):  
R. McTasney ◽  
R. A. Rio ◽  
W. A. Troha

After turbine engine is overhauled at Oklahoma City Air Logistics Center (OC-ALC) or at San Antonio Air Logistics Center (SA-ALC), it is run in the test cell before shipment. While in the test cell, final adjustments are made to the engine. One of these adjustments is the dynamic vibration balance of the engine. This adjustment is referred to as a trim balance. The current trim balance procedures in use at OC-ALC require the engine to be in the test cell from 4 to 6 hr. This paper presents a new automated procedure which has demonstrated a reduction in test cell time by 60 to 80 percent. In addition, engines which cannot be trim balanced must be returned to the overhaul line for partial disassembly and rework. The diagnostic guidance provided to the rework line is highly subjective and dependent on operator experience. Uncertain problem definition often results in rejecting the same engine several times. The new procedure described in this paper shows promise for automating vibration diagnostics. This would allow definitive guidance to be provided to the rework line and reduce repeated rejects of the same engine. The Automated Trim Balancing and Diagnostic Systems as designed for OC-ALC and SA-ALC have a projected multi-million dollar savings for the Air Force.

2020 ◽  
Vol 50 (1) ◽  
pp. 171-192
Author(s):  
Henryk Borowczyk ◽  
Jarosław Spychała

AbstractThe paper presents issues related to the design of an expert diagnostic system of turbine engine functional units. Dedicated diagnostic stations and on-board flight data recorders are the sources of diagnostic signals. The signals were parameterized or identified dynamic models to get a compact representation in the form of a set of parameters. The set of diagnostic parameters was subjected to integer encoding. On this basis, a multi-valued diagnostic model describing the relationship between the set of faults and the set of symptoms (code values of diagnostic parameters) was determined. The proposed approach can be used in the design of expert diagnostic systems for propulsion units of any aircraft.


1976 ◽  
Author(s):  
M. H. Chopin

The preparation for and conduct of the first flight by the U. S. Air Force of a turbine engine fan stage fabricated of advanced composite materials is discussed. Composite material properties and basic design philosophy is presented along with preliminary flight evaluation results. This is the first application of filamentary-reinforced metal matrix composites to a turbine engine structural component.


Author(s):  
D. Salinas ◽  
E. E. Cooper

A numerical simulation of the aerothermal characteristics of a gas turbine engine test cell is presented. The three-dimensional system is modeled using the PHOENICS computational fluid dynamics code. Results predict the velocity field, temperatures, pressures, kinetic energy of turbulence, and dissipation rates of turbulent kinetic energy. Numerical results from two versions, a cartesian coordinate model and a body fitted coordinate model, are compared to experimental data. The comparison shows good quantitative and very good qualitative agreement, suggesting that numerical modeling would be useful in the preliminary design of gas turbine test facilities.


Sign in / Sign up

Export Citation Format

Share Document