Project Title:

Adaptive Closed-Loop System for Control of Combustor Pattern Factor (71 14-940)

  	  94-1	01.03	0003

  	  Adaptive Closed-Loop System for Control of Combustor Pattern 
  Factor
  	  (71 14-940)

Abstract:

This proposal describes a program to experimentally 
demonstrate an 
adaptive closed-loop control system for real-time control of 
the 
exit temperature distribution in gas-turbine combustors. The 

proposed concept takes advantage of new technologies 
associated 
with adaptive signal processing and flow control to create 
a 
completely new engine control system. The system is based on 
a 
multi-input/output controller using an adaptive neural 
network. 
Demonstration experiments will be performed in an existing 
small-
scale spray combustion facility modified to accommodate 
dilution 
air actuators and temperature sensors. Proof-of-principle 
experiments to control the combustor exit temperature profile will 
be demonstrated in this simplified geometry. Conclusions drawn from 
these experiments will be used to identify control system 
requirements for full scale gas-turbine applications. The Phase II 
program will then design, fabricate, and test a scaled-up control 
system on a larger combustor with eventual testing to be performed 
on a designated NASA gas-turbine combustor sector rig.

The proposed innovation is applicable to both commercial and 
military gas-turbine combustion systems including both stationary 
and propulsion related applications. The system will increase gas-
turbine service life by controlling the thermal stress associated 
with turbine blade wear. Successful implementation of the proposed 
system in commercial aircraft propulsion units will represent a 
significant savings to the airline industry by reducing turbine hot 
section service and maintenance costs.

Key Words

Physical Sciences Inc.
20 New England Business Center
Andover, MA 01810-1077