System and method of non-intrusive thrust measurement

Patent metadata

Field	Value
Publication number	US-10364698-B2
Application number	US-201715617028-A
Country	US
Kind code	B2
Filing date	Jun 8, 2017
Priority date	Jun 10, 2016
Publication date	Jul 30, 2019
Grant date	Jul 30, 2019

Abstract

A system and method of non-intrusive thrust measurement of a gas turbine engine. The system comprises a transmitter disposed at a boundary of fluid flow and at least one receiver adapted to receive transmissions from the transmitter. A processor is coupled to the receivers to determine a parameter from a characteristic of the transmission at the receiver suite and adapted to determine a thrust parameter from the parameter. A method for non-intrusively measuring engine thrust includes transmitting a wave across the exhaust plume, receiving the transmitted wave and determining a measurement parameter of the exhaust plume based on a characteristic of the received wave, and comparing the measurement parameter to a reference parameter and determining the thrust based on the comparison.

First claim

What is claimed is:

1. A non-intrusive thrust measurement system comprising:
a boundary defining a passage along an axis adapted to contain a fluid flowing from upstream to downstream;
an acoustic transmitter at said boundary;
a receiver suite at said boundary and adapted to receive a transmission from the transmitter;
a processor in communication with the transmitter and receiver suite adapted to determine a parameter from a characteristic of the transmission at the receiver suite and adapted to determine a thrust parameter from the parameter;
wherein the receiver suite comprises:
a first acoustic receiver at said boundary and adapted to receive a transmission from the acoustic transmitter;
a second acoustic receiver at said boundary and adapted to receive the transmission from the at least one acoustic transmitter;
wherein the characteristic determined by the processor is the time of arrival of the transmission at the first receiver and second receiver;
wherein the first and second acoustic receivers and the acoustic transmitter define a plane substantially parallel to the axis and wherein the second acoustic receiver is downstream from the first acoustic receiver and the first acoustic receiver is downstream from the acoustic transmitter.

2. The system of claim 1 , wherein the acoustic transmitter operates at 40 khz and above.

3. The system of claim 1 , wherein the processor is further adapted to compare the parameter to a baseline in determining the thrust parameter.

4. The system of claim 1 , wherein the passage is a bypass flow.

Assignees

• Rolls Royce Nam Tech Inc

Inventors

• Hodge C Edward

Classifications

• G01L5/133

  for measuring thrust of propulsive devices, e.g. of propellers (aeroplanes B64C; marine propulsion B63H; jet-engines F02K) · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• G01P5/245 Primary

  by measuring transit time of acoustical waves (measuring propagation velocity of acoustical waves per se G01H5/00) · CPC title

• G01M15/00

  Testing of engines · CPC title

• G01F1/667

  Arrangements of transducers for ultrasonic flowmeters; Circuits for operating ultrasonic flowmeters · CPC title