Device for measuring aerodynamic magnitudes intended to be placed in a flow passage of a turbine engine

Patent metadata

Field	Value
Publication number	US-10138754-B2
Application number	US-201615348824-A
Country	US
Kind code	B2
Filing date	Nov 10, 2016
Priority date	Nov 12, 2015
Publication date	Nov 27, 2018
Grant date	Nov 27, 2018

Abstract

The present invention relates to a device for measuring aerodynamic magnitudes ( 1 ) intended to be placed transversally in a flow passage ( 12, 13 ) of a turbine engine comprising:
an upstream body ( 2 ) having a profile of general cylindrical shape defining a leading edge ( 5 ) a plurality of sensors ( 4 ), the instrumentation lines ( 45 ) of the sensors being placed in the body ( 2 ), the sensitive elements ( 41 ) of the sensors extending at the leading edge ( 5 ); a downstream fairing ( 3 ) mounted on the upstream body ( 2 ) and defining a trailing edge ( 6 ); the downstream fairing ( 3 ) comprising, in the longitudinal direction of the upstream body ( 2 ), several sections ( 35 ) fixed independently of each other to the body ( 2 ), two successive sections ( 35 ) being connected by a flexible junction ( 37 ).

First claim

The invention claimed is:

1. A device for measuring aerodynamic magnitudes intended to be placed transversally in a flow passage of a turbine engine comprising:
an upstream body having a profile of general cylindrical shape defining a leading edge
a plurality of sensors including instrumentation lines and sensitive elements, the instrumentation lines of the sensors being placed in the body, the sensitive elements of the sensors extending at the leading edge;
a downstream fairing mounted on the upstream body and defining a trailing edge;
the device for measuring aerodynamic magnitude wherein said downstream fairing comprises, in the longitudinal direction of the upstream body bearing the sensors, several sections of downstream fairing fixed independently of each other to the body, two successive sections being connected by a junction which in the longitudinal direction of the upstream body is more flexible than the sections.

2. The device for measuring aerodynamic magnitudes, according to claim 1 , wherein the downstream fairing is formed of two sections.

3. The device for measuring aerodynamic magnitudes, according to claim 1 , wherein the sections have, in the longitudinal direction of the upstream body, a Young's modulus of over 50 GPa.

4. The device for measuring aerodynamic magnitudes, according to claim 1 , wherein the flexible junction has, in the longitudinal direction of the upstream body, a Young's modulus of less than 1 GPa.

5. The device for measuring aerodynamic magnitudes, according to claim 1 , wherein the flexible junction is made of elastomer.

6. The device for measuring aerodynamic magnitudes, according to claim 1 , wherein the sections are made of metal.

7. The device for measuring aerodynamic magnitudes, according to claim 1 , wherein the downstream fairing is fixed to the upstream body by shrinking.

8. The device for measuring aerodynamic magnitudes, according to claim 1 , wherein the downstream fairing is fixed to the upstream body by means of pins.

9. A method for determining the position of at least one flexible junction of a device for measuring aerodynamic magnitudes,
wherein said device is intended to be placed transversally in a flow passage of a turbine engine and comprises:
an upstream body having a profile of general cylindrical shape defining a leading edge
a plurality of sensors including instrumentation lines and sensitive elements, the instrumentation lines of the sensors being placed in the body, the sensitive elements of the sensors extending at the leading edge;
a downstream fairing mounted on the upstream body and defining a trailing edge;
wherein said downstream fairing comprises, in the longitudinal direction of the upstream body bearing the sensors, several sections of downstream fairing fixed independently of each other to the body, two successive sections being connected by a junction which in the longitudinal direction of the upstream body is more flexible than the sections,
wherein it comprises steps of:
determining the vibratory frequencies in the flow passage;
determining the position of at least one flexible junction in the longitudinal direction of the upstream body and/or the number and/or the position of the pins, such that at least one specific frequency of the device for measuring aerodynamic magnitudes does not coincide with the vibratory frequencies in the flow passage.

10. A method for testing a turbine engine, comprising placing a device for measuring aerodynamic magnitudes in a flow passage of the turbine engine wherein said device is for placing transversally in the flow passage of the turbine engine and comprises:
an upstream body having a profile of general cylindrical shape defining a leading edge
a plurality of sensors including instrumentation lines and sensitive elements, the instrumentation lines of the sensors being placed in the body, the sensitive elements of the sensors extending at the leading edge;
a downstream fairing mounted on the upstream body and defining a trailing edge;
wherein said downstream fairing comprises, in the longitudinal direction of the upstream body bearing the sensors, several sections of downstream fairing fixed independently of each other to the body, two successive sections being connected by a junction which in the longitudinal direction of the upstream body is more flexible than the sections.

11. A method for determining the number and/or of the position of the pins in a device for measuring aerodynamic magnitudes,
wherein said device is intended to be placed transversally in a flow passage of a turbine engine and comprises:
an upstream body having a profile of general cylindrical shape defining a leading edge;
a plurality of sensors including instrumentation lines and sensitive elements, the instrumentation lines of the sensors being placed in the body, the sensitive elements of the sensors extending at the leading edge;
a downstream fairing mounted on the upstream body and defining a trailing edge;
wherein said downstream fairing comprises, in the longitudinal direction of the upstream body bearing the sensors, several sections of downstream fairing fixed independently of each other to the body, two successive sections being connected by a junction which in the longitudinal direction of the upstream body is more flexible than the sections,
wherein the downstream fairing is fixed to the upstream body by means of pins of a device for measuring aerodynamic magnitudes,
wherein said method comprises steps of:
determining the vibratory frequencies in the flow passage;
determining the position of at least one flexible junction in the longitudinal direction of the upstream body and/or the number and/or the position of the pins, such that at least one specific frequency of the device for measuring aerodynamic magnitudes does not coincide with the vibratory frequencies in the flow passage.

Assignees

• Safran Aircraft Engines

Inventors

• Giordan Jeremy
• KOCKENPO Bernard Joseph Florian

Classifications

• G01F1/46

  Pitot tubes · CPC title

• F05D2270/80

  Devices generating input signals, e.g. transducers, sensors, cameras or strain gauges · CPC title

• F01D5/14

  Form or construction (selecting particular materials, measures against erosion or corrosion F01D5/28) · CPC title

• F05D2220/30

  in turbines · CPC title

• G01D11/245

  Housings for sensors · CPC title