System and method for gathering flight load data

Patent metadata

Field	Value
Publication number	US-11506571-B2
Application number	US-201916564862-A
Country	US
Kind code	B2
Filing date	Sep 9, 2019
Priority date	Sep 9, 2019
Publication date	Nov 22, 2022
Grant date	Nov 22, 2022

Abstract

A method for gathering flight load data for a gas turbine engine includes providing a plurality of blocker doors rotatably mounted to a translating sleeve and a plurality of blocker door islands, each blocker door island disposed between circumferentially adjacent blocker doors of the plurality of blocker doors and mounted to at least one mounting point of the translating sleeve, wherein a blocker door island of the plurality of blocker door islands is a data acquisition unit; and connecting the data acquisition unit to at least one sensor in communication with the translating sleeve.

First claim

What is claimed is:

1. A method for gathering flight load data for a gas turbine engine, the method comprising:
providing a plurality of blocker doors, rotatably mounted to a translating sleeve and providing a plurality of blocker door islands, each blocker door island disposed between circumferentially adjacent blocker doors of the plurality of blocker doors and mounted to at least one mounting point of the translating sleeve, wherein a blocker door island of the plurality of blocker door islands is a data acquisition unit, the data acquisition unit selectively mounted to a respective mounting point of the at least one mounting point; and
connecting the data acquisition unit to at least one sensor mounted to an interior surface of the translating sleeve, the interior surface forming at least a portion of a bypass flow path of the gas turbine engine.

2. The method of claim 1 , wherein the step of providing the plurality of blocker door islands includes removing a first blocker door island of the plurality of blocker door islands from the respective mounting point of the at least one mounting point and selectively mounting the data acquisition unit to the respective mounting point of the at least one mounting point.

3. The method of claim 2 , further comprising gathering flight load data from the at least one sensor with the data acquisition unit.

4. The method of claim 3 , further comprising storing the flight load data with the data acquisition unit.

5. The method of claim 4 , further comprising:
removing the data acquisition unit from the translating sleeve subsequent to storing the flight load data; and
reading the flight load data stored in the data acquisition unit.

6. The method of claim 1 , wherein the gas turbine engine includes a nacelle comprising the translating sleeve and a nacelle portion axially adjacent the translating sleeve, the translating sleeve and the nacelle portion disposed about an axial centerline of the gas turbine engine.

7. The method of claim 6 , wherein the translating sleeve is configured to axially translate relative to the nacelle portion and the nacelle portion is axially fixed relative to the gas turbine engine.

8. The method of claim 7 , wherein the data acquisition unit is in communication with the at least one sensor via a wire.

9. The method of claim 8 , wherein the data acquisition unit and the at least one sensor are configured to axially translate with the translating sleeve.

10. The method of claim 1 , wherein the at least one sensor includes one or more of a temperature sensor or a pressure sensor.

11. A system for gathering flight load data of a gas turbine engine, the system comprising:
a thrust reverser comprising a translating sleeve and an inner barrel, the thrust reverser including an interior surface forming at least a portion of a bypass flow path of the gas turbine engine;
a plurality of blocker doors hingedly attached to the thrust reverser;
a plurality of blocker door islands, each blocker door island disposed between circumferentially adjacent blocker doors of the plurality of blocker doors and mounted to at least one mounting point of the thrust reverser; and
at least one sensor mounted to the interior surface of the translating sleeve;
wherein a blocker door island of the plurality of blocker door islands is a data acquisition unit and the data acquisition unit is connected to the at least one sensor, the data acquisition unit selectively mounted to a respective mounting point of the at least one mounting point.

12. The system of claim 11 , wherein the gas turbine engine includes a nacelle comprising the translating sleeve and a nacelle portion axially adjacent the translating sleeve, the translating sleeve and the nacelle portion disposed about an axial centerline of the gas turbine engine.

13. The system of claim 12 , wherein the translating sleeve is configured to axially translate relative to the nacelle portion and the nacelle portion is axially fixed relative to the gas turbine engine.

14. The system of claim 11 , wherein the at least one sensor includes one or more of a temperature sensor or a pressure sensor.

15. The system of claim 11 , wherein the data acquisition unit is in communication with the at least one sensor via a wire.

16. The system of claim 15 , wherein the data acquisition unit and the at least one sensor are configured to axially translate with the translating sleeve.

17. A gas turbine engine comprising:
an engine core having an axial centerline; and
a nacelle surrounding the engine core, the nacelle comprising a thrust reverser and an axially fixed nacelle portion axially adjacent the thrust reverser, the thrust reverser comprising:
a translating sleeve, the translating sleeve including an interior surface forming at least a portion of a bypass flow path with the bypass flow path between the engine core and the nacelle;
a plurality of blocker doors rotatably mounted to an interior surface of the translating sleeve;
a plurality of blocker door islands, each blocker door island disposed between circumferentially adjacent blocker doors of the plurality of blocker doors and mounted to at least one mounting point of the translating sleeve; and
at least one sensor mounted to the interior surface of the translating sleeve;
wherein a blocker door island of the plurality of blocker door islands is a data acquisition unit and the data acquisition unit is connected to the at least one sensor, the data acquisition unit selectively mounted to a respective mounting point of the at least one mounting point.

18. The gas turbine engine of claim 17 , wherein the data acquisition unit has an outer radial side mounted to the translating sleeve and an inner radial side opposite the outer radial side and wherein the inner radial side defines a portion of the bypass flow path of the gas turbine engine.

19. The gas turbine engine of claim 17 , wherein the data acquisition unit and the at least one sensor are configured to axially translate with the translating sleeve.

20. The gas turbine engine of claim 17 , wherein the at least one sensor includes one or more of a temperature sensor or a pressure sensor.

Assignees

• Rohr Inc

Inventors

• Kestler Steven M
• Teets Kevin W

Classifications

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title

• G01H1/006

  of the rotor of turbo machines · CPC title

• B64F5/60

  Testing or inspecting aircraft components or systems · CPC title

• G01M15/14 Primary

  Testing gas-turbine engines or jet-propulsion engines · CPC title

• G01M15/048

  by monitoring temperature · CPC title