Miniature high-frequency temperature-insensitive fiber optic pressure sensor for gas turbine engine applications

1999 ◽  
Author(s):  
Jiangdong Deng ◽  
Shenru Li ◽  
Hai Xiao ◽  
Wei Huo ◽  
Paul G. Duncan ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Pressure Sensor ◽  
High Frequency ◽  
Fiber Optic ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Frequency Temperature

Fiber optic pressure sensor system for gas turbine engine control

1991 ◽  
Author(s):  
Laurence N. Wesson ◽  
Nellie L. Cabato ◽  
Nicholson L. Pine ◽  
Victor J. Bird
Keyword(s):  
Gas Turbine ◽  
Pressure Sensor ◽  
Fiber Optic ◽  
Gas Turbine Engine ◽  
Sensor System ◽  
Engine Control ◽  
Turbine Engine

A One Dimensional, Time Dependent Inlet / Engine Numerical Simulation for Aircraft Propulsion Systems

1997 ◽  
Author(s):  
Doug Garrard ◽  
Milt Davis ◽  
Steve Wehofer ◽  
Gary Cole
Keyword(s):  
Numerical Simulation ◽  
Gas Turbine ◽  
High Frequency ◽  
Gas Turbine Engine ◽  
Simulation System ◽  
Time Dependent ◽  
Propulsion Systems ◽  
Turbine Engine ◽  
One Dimensional ◽  
Supersonic Inlet

The NASA Lewis Research Center (LeRC) and the Arnold Engineering Development Center (AEDC) have developed a closely coupled computer simulation system that provides a one dimensional, high frequency inlet / engine numerical simulation for aircraft propulsion systems. The simulation system, operating under the LeRC-developed Application Portable Parallel Library (APPL), closely coupled a supersonic inlet with a gas turbine engine. The supersonic inlet was modeled using the Large Perturbation Inlet (LAPIN) computer code, and the gas turbine engine was modeled using the Aerodynamic Turbine Engine Code (ATEC). Both LAPIN and ATEC provide a one dimensional, compressible, time dependent flow solution by solving the one dimensional Euler equations for the conservation of mass, momentum, and energy. Source terms are used to model features such as bleed flows, turbomachinery component characteristics, and inlet subsonic spillage while unstarted. High frequency events, such as compressor surge and inlet unstart, can be simulated with a high degree of fidelity. The simulation system was exercised using a supersonic inlet with sixty percent of the supersonic area contraction occurring internally, and a GE J85-13 turbojet engine.

Epoxy-free high-temperature fiber optic pressure sensors for gas turbine engine applications

2004 ◽  
Author(s):  
Juncheng Xu ◽  
Gary Pickrell ◽  
Bing Yu ◽  
Ming Han ◽  
Yizheng Zhu ◽  
...  
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Fiber Optic ◽  
Pressure Sensors ◽  
Gas Turbine Engine ◽  
Turbine Engine

Fiber optic speed sensor for advanced gas turbine engine control

1991 ◽  
Author(s):  
Deepak Varshneya ◽  
John L. Maida, Jr. ◽  
Mark A. Overstreet
Keyword(s):  
Gas Turbine ◽  
Fiber Optic ◽  
Gas Turbine Engine ◽  
Engine Control ◽  
Turbine Engine ◽  
Speed Sensor

Commercial Demonstration of Un-Cooled Pressure Sensor for Gas-Turbine Engine Monitoring

2007 ◽  
Author(s):  
Matthew E. Palmer ◽  
Matthew A. Davis ◽  
Robert S. Fielder
Keyword(s):  
Gas Turbine ◽  
Static Pressure ◽  
Fiber Optic ◽  
Field Trials ◽  
Gas Turbine Engine ◽  
Fiber Optic Sensor ◽  
Maximum Temperature ◽  
Sensor Calibration ◽  
Turbine Engine ◽  
Optic Sensor

An un-cooled fiber-optic sensor has been developed for the purpose of gas turbine engine health monitoring. These sensors were developed over the course of 2 SBIR and 1 STTR Phase II’s, each contributing to an advancement in the sensor’s development. Real time direct monitoring of combustion pressure within aircraft turbines will enable more efficient, lower emission designs, through active control of the fuel supply. Sensor prototypes have been demonstrated to operate at greater than 1922°F (1050°C) and 500psig in laboratory experimentation. A co-located measurement system enabled the team to calibrate an alpha prototype sensor over a range of 70°F to 1840°F (20–1000°C) and 0-500psig with an error less than 0.37% Full Scale (FS) over the entire sensor calibration envelope. Previous iterations of this sensor were prototyped and installed into an operating, specially modified, aerospace gas turbine engine immediately after the 1st stage turbine. In this engine the alpha fiber-optic sensor measured dynamic pressures of +/- 0.5 psi while exposed to a maximum temperature of 932.9°F (500.5°C) and a maximum static pressure of 15.4 psig during operation. Finally, another alpha prototype was demonstrated in field trials at a customer facility in two combustors. During these trials the sensor usefully captured hum and rumble oscillations while measuring pressures reasonably accurately at temperatures up to 1652°F (900°C).

Fiber Optic Speed Sensor For Gas Turbine Engine Control

1990 ◽  
Author(s):  
Mark A. Overstreet ◽  
Victor J. Bird ◽  
Deepak Varshneya ◽  
John L. Maida
Keyword(s):  
Gas Turbine ◽  
Fiber Optic ◽  
Gas Turbine Engine ◽  
Engine Control ◽  
Turbine Engine ◽  
Speed Sensor
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