skip to main content
OSTI.GOV title logo U.S. Department of Energy
Office of Scientific and Technical Information

Title: Non-intrusive measurement of hot gas temperature in a gas turbine engine

Abstract

A method and apparatus for operating a gas turbine engine including determining a temperature of a working gas at a predetermined axial location within the engine. An acoustic signal is encoded with a distinct signature defined by a set of predetermined frequencies transmitted as a non-broadband signal. Acoustic signals are transmitted from an acoustic transmitter located at a predetermined axial location along the flow path of the gas turbine engine. A received signal is compared to one or more transmitted signals to identify a similarity of the received signal to a transmitted signal to identify a transmission time for the received signal. A time-of-flight is determined for the signal and the time-of-flight for the signal is processed to determine a temperature in a region of the predetermined axial location.

Inventors:
; ; ; ;
Publication Date:
Research Org.:
SIEMENS ENERGY, INC. Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1326807
Patent Number(s):
9,453,784
Application Number:
14/017,386
Assignee:
SIEMENS ENERGY, INC. (Orlando, FL) NETL
DOE Contract Number:
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 2013 Sep 04
Country of Publication:
United States
Language:
English
Subject:
47 OTHER INSTRUMENTATION

Citation Formats

DeSilva, Upul P., Claussen, Heiko, Yan, Michelle Xiaohong, Rosca, Justinian, and Ulerich, Nancy H.. Non-intrusive measurement of hot gas temperature in a gas turbine engine. United States: N. p., 2016. Web.
DeSilva, Upul P., Claussen, Heiko, Yan, Michelle Xiaohong, Rosca, Justinian, & Ulerich, Nancy H.. Non-intrusive measurement of hot gas temperature in a gas turbine engine. United States.
DeSilva, Upul P., Claussen, Heiko, Yan, Michelle Xiaohong, Rosca, Justinian, and Ulerich, Nancy H.. 2016. "Non-intrusive measurement of hot gas temperature in a gas turbine engine". United States. doi:. https://www.osti.gov/servlets/purl/1326807.
@article{osti_1326807,
title = {Non-intrusive measurement of hot gas temperature in a gas turbine engine},
author = {DeSilva, Upul P. and Claussen, Heiko and Yan, Michelle Xiaohong and Rosca, Justinian and Ulerich, Nancy H.},
abstractNote = {A method and apparatus for operating a gas turbine engine including determining a temperature of a working gas at a predetermined axial location within the engine. An acoustic signal is encoded with a distinct signature defined by a set of predetermined frequencies transmitted as a non-broadband signal. Acoustic signals are transmitted from an acoustic transmitter located at a predetermined axial location along the flow path of the gas turbine engine. A received signal is compared to one or more transmitted signals to identify a similarity of the received signal to a transmitted signal to identify a transmission time for the received signal. A time-of-flight is determined for the signal and the time-of-flight for the signal is processed to determine a temperature in a region of the predetermined axial location.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = 2016,
month = 9
}

Patent:

Save / Share:
  • An apparatus for controlling operation of a gas turbine engine including at least one acoustic transmitter/receiver device located on a flow path boundary structure. The acoustic transmitter/receiver device includes an elongated sound passage defined by a surface of revolution having opposing first and second ends and a central axis extending between the first and second ends, an acoustic sound source located at the first end, and an acoustic receiver located within the sound passage between the first and second ends. The boundary structure includes an opening extending from outside the boundary structure to the flow path, and the second endmore » of the surface of revolution is affixed to the boundary structure at the opening for passage of acoustic signals between the sound passage and the flow path.« less
  • Performance of a gas turbine engine is monitored by computing a mass flow rate through the engine. Acoustic time-of-flight measurements are taken between acoustic transmitters and receivers in the flow path of the engine. The measurements are processed to determine average speeds of sound and gas flow velocities along those lines-of-sound. A volumetric flow rate in the flow path is computed using the gas flow velocities together with a representation of the flow path geometry. A gas density in the flow path is computed using the speeds of sound and a measured static pressure. The mass flow rate is calculatedmore » from the gas density and the volumetric flow rate.« less
  • The power available from a gas turbine engine is accurately determined by correcting predicted torque and gas generator speed for variations from normal of engine performance. The correction function is adaptively updated on-line by comparing actual and predicted values of torque and speed, storing any differences and summing the stored differences with the predicted values during the determination of power available.
  • This patent describes a combustion turbine engine. It comprises: an inlet, an outlet, and a flow path communicating a flow of fluid therebetween, the engine including a rotatable compressor inducting a flow of ambient air via the inlet and delivering this air pressurized to a combustor, means delivering a flow of fuel to the combustor to support combustion in the pressurized air to produce a flow of high temperature combustion products, and a turbine expanding the combustion products for discharge into ambient air via the outlet to derive mechanical power therefrom driving the compressor.
  • A high temperature turbine engine includes a hybrid ceramic/metallic rotor member having ceramic/metal joint structure. The disclosed joint is able to endure higher temperatures than previously possible, and aids in controlling heat transfer in the rotor member.