Secondary systems and methods of control for variable area fan nozzles

Patent metadata

Field	Value
Publication number	US-9803586-B1
Application number	US-201615169155-A
Country	US
Kind code	B1
Filing date	May 31, 2016
Priority date	May 31, 2016
Publication date	Oct 31, 2017
Grant date	Oct 31, 2017

Abstract

A control system for a variable area fan nozzle (VAFN) is disclosed. The VAFN may have a plurality of petals and may be for use with a gas turbine engine. The control system may include a primary system configured to acquire primary data indicative of an operating condition of the VAFN, a secondary system configured to acquire secondary data indicative of a current operating condition of the gas turbine engine, and a control module in operative communication with the primary system and the secondary system. The control module may be configured to: determine a nozzle area of the VAFN based at least in part on the primary data, adjust the determined nozzle area based on the secondary data, and position the plurality of petals according to the adjusted nozzle area.

First claim

What is claimed is:

1. A control system for a variable area fan nozzle (VAFN) having a plurality of petals, the VAFN for use with a gas turbine engine, the control system comprising:
a primary system configured to acquire primary data indicative of an operating condition of the VAFN;
a secondary system configured to acquire secondary data indicative of a current operating condition of the gas turbine engine; and
a control module in operative communication with the primary system and the secondary system, the control module configured to:
determine a nozzle area of the VAFN based at least in part on the primary data,
adjust the determined nozzle area based on the secondary data, and
position the plurality of petals according to the adjusted nozzle area.

2. The control system of claim 1 , wherein the secondary data includes data indicative of a backpressure of the gas turbine engine.

3. The control system of claim 2 , wherein the secondary system includes at least one pressure sensor configured to determine the backpressure of the gas turbine engine.

4. The control system of claim 3 , wherein the at least one pressure sensor is disposed proximate an aft end of a core engine nacelle of the gas turbine engine.

5. The control system of claim 1 , wherein the secondary data includes data indicative of a fan blade strain of the gas turbine engine.

6. The control system of claim 5 , wherein the secondary system includes at least one strain sensor configured to determine the fan blade strain of the gas turbine engine.

7. The control system of claim 6 , wherein the at least one strain sensor comprises a fiber optic strain sensor disposed on a fan blade of the gas turbine engine.

8. The control system of claim 1 , wherein the control module is further configured to determine an operational transient of the gas turbine engine based on the secondary data.

9. The control system of claim 8 , wherein the control module is further configured to send a signal to alert aircraft crew members of the operational transient.

10. The control system of claim 9 , wherein the control module is further configured to move the plurality of petals to a failsafe position when the secondary data indicates the operational transient.

11. An aircraft, comprising:
a gas turbine engine;
a variable area fan nozzle (VAFN) mounted to a downstream end of the gas turbine engine, the VAFN including a plurality of petals and at least one actuator configured to move the plurality of petals; and
a control system in operative communication with the gas turbine engine and the VAFN, the control system including:
at least one pressure sensor configured to determine a backpressure of the gas turbine engine;
at least one strain sensor configured to determine a fan blade strain of the gas turbine engine; and
a control module in operative communication with the at least one pressure sensor, the at least one strain sensor, and a primary system configured to configured to acquire primary data indicative of an operating condition of the VAFN, the control module configured to:
calculate a real-time nozzle area of the VAFN based at least in part on the primary data,
generate an actuator command based at least in part on the real-time nozzle area and a predetermined table of nozzle areas preprogrammed into a memory of the control module,
modify the actuator command based on at least one of the determined backpressure and the determined fan blade strain, and
send the modified actuator command to the at least one actuator of the VAFN to adjust the plurality of petals.

12. The aircraft of claim 11 , wherein the at least one pressure sensor comprises one of a LIDAR based pressure sensor or a pitot tube.

13. The aircraft of claim 11 , wherein the control module is implemented via an engine electronic control and a VAFN control unit.

14. The aircraft of claim 13 , wherein the control module includes a model based controller configured to estimate a nozzle area of the VAFN when primary data is unavailable.

15. The aircraft of claim 14 , wherein the model based controller includes a learning algorithm for estimating the nozzle area based on inputs into the engine electronic control.

16. The aircraft of claim 15 , wherein the control module is further configured to determine an operational transient of the gas turbine engine if the estimated nozzle area from the model based controller is outside a predetermined margin of a calculated nozzle area determined by the VAFN control unit.

17. A method for controlling a nozzle area of a variable area fan nozzle (VAFN) having a plurality of petals, the VAFN for use with a gas turbine engine, the method comprising:
acquiring primary data indicative of an operating condition of the VAFN;
acquiring secondary data indicative of a backpressure and a fan blade strain of the gas turbine engine;
calculating the nozzle area of the VAFN based on the primary data;
generating a desired nozzle area based at least in part on a predetermined table of nozzle areas;
producing an actuator command based on a difference between the calculated nozzle area and the desired nozzle area;
adjusting the actuator command based on the secondary data; and
sending the adjusted actuator command to the VAFN to move the plurality of petals, the calculating, generating, producing, adjusting, and sending being performed by a control module associated with the VAFN and the gas turbine engine.

18. The method of claim 17 , further comprising learning a nozzle area of the VAFN based on inputs into an engine electronic control of the gas turbine engine, the learning being performed by a model based controller of the control system.

19. The method of claim 17 , further comprising using the secondary data to determine an operational transient of the gas turbine engine.

20. The method of claim 19 , further comprising alerting aircraft crew members of the operational transient and moving the plurality of petals of the VAFN to a failsafe position when the operational transient is determined.

Assignees

• Boeing Co

Inventors

• Jackowski Jason J
• Karnofski Kent E
• Foutch David W

Classifications

• F02K3/04

  the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F05D2270/3013

  Outlet pressure · CPC title

• F04D29/542

  Bladed diffusers (fixing blades to stators F01D9/042) · CPC title

• F05D2270/71

  synthesized, i.e. parameter computed by a mathematical model · CPC title