Fiber-optic system for checking the acoustical parameters of gas-turbine engine flow-through passages

2015 ◽  
Author(s):  
Vasiliy Y. Vinogradov ◽  
Oleg G. Morozov ◽  
Ilnur I. Nureev ◽  
Artem A. Kuznetzov
Keyword(s):  
Gas Turbine ◽  
Fiber Optic ◽  
Gas Turbine Engine ◽  
Optic System ◽  
Acoustical Parameters ◽  
Turbine Engine ◽  
Flow Through ◽  
Fiber Optic System

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

Towards Large Eddy Simulation of Rotating Turbomachinery for Variable Speed Gas Turbine Engine Operation

2019 ◽  
Author(s):  
Nishan Jain ◽  
Luis Bravo ◽  
Dokyun Kim ◽  
Muthuvel Murugan ◽  
Anindya Ghoshal ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Operating Conditions ◽  
Variable Speed ◽  
Solution Quality ◽  
Engine Operation ◽  
Turbine Engine ◽  
Design Point ◽  
Large Eddy ◽  
Flow Through

Abstract In this work, massively parallel wall-modeled Large Eddy Simulations (LES) are conducted to simulate flow through a single stage power turbine sector of a gas-turbine engine under realistic operating conditions. The numerical framework in the current work uses finite volume based compressible CharLES solver that utilizes a moving Voronoi diagram based grid generation. To test grid sensitivity and evaluate the capability of the solver in predicting turbomachinery flows, three grids of varying resolution are used to simulate flow through the baseline gas-turbine under design operating conditions. After assessing the flow solution quality and establishing simulation parameters, LES simulations are conducted to investigate the performance of gas-turbine at off-design conditions. The conditions include the rotor design point at 100% speed, and off-design points at 75%, and 50% speeds subject to high temperatures from the combustor exit flow. The results showed that the internal flow becomes highly unsteady as the rotational speed of rotor deviates from the design point leading to reduced aerodynamic performance. This study demonstrates that the current framework is able to robustly simulate the unsteady flow in a three-dimensional moving rotor environment towards the design of variable speed gas-turbine engines for US Army Future Vertical Lift program.

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

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

Novel gap inspection method for gas turbine with total fiber optic system

2001 ◽  
Author(s):  
Jun Wang ◽  
Yong Zhao ◽  
Lihua Liu ◽  
Pengsheng Li
Keyword(s):  
Gas Turbine ◽  
Fiber Optic ◽  
Optic System ◽  
Inspection Method ◽  
Fiber Optic System
Sign in / Sign up

Export Citation Format

Share Document