FMU MOUNTED EEC FOR SMALL AIRCRAFT ENGINE APPLICATIONS

• US 20120095663A1
• Filed: 10/14/2010
• Published: 04/19/2012
• Est. Priority Date: 10/14/2010
• Status: Abandoned Application

• Current Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Roy, Kevin P., Zebrowski, Thaddeus J.
• Application Number:
  US12/904,767
• Publication Number:
  US 20120095663A1
• Time in Patent Office: Days
• US Class Current: 701/100
• CPC Class Codes: F02C 9/263 by means of fuel metering valves
• CPC Class Codes: F02C 9/28 Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed F02C9/30 - F02C9/38, F02C9/44 take precedence
• CPC Class Codes: F02C 9/48 Control of fuel supply conjointly with another control of the plant with nozzle section control F02K1/17
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A fuel metering unit (FMU) for an aircraft engine includes an effector and an electronic engine controller (EEC). The effector is electrically connected to the EEC to adjust a rate of fuel flowing into the engine. The adjustment is in response to a control signal sent from the EEC. The control signal sent from the EEC is responsive to an engine sensor signal and to airframe sensor information.

Claims

1. A fuel metering unit (FMU) for an aircraft engine, the FMU comprising:

an effector; and

an electronic engine controller (EEC);

wherein the effector is electrically connected to the EEC to adjust one of a rate of fuel flowing into the engine, a stator vane position, and a rate of bleed air flowing from an engine compressor in response to a control signal sent from the EEC; and

the control signal sent from the EEC is responsive to an engine sensor signal and to airframe sensor information.

2. The FMU of claim 1, wherein the FMU is contained within a single housing.

3. The FMU of claim 1, wherein the FMU further comprises a cooling device in thermal contact with the EEC.

4. The FMU of claim 1, wherein the airframe sensor information is airframe sensor digital data sent by an airframe data concentrator (ADC) over a digital bus electrically connecting the ADC to the EEC.

5. The FMU of claim 1, further comprising analog-to-digital conversion electronics to convert airframe analog signals to digital data, wherein the EEC and the analog-to-digital conversion electronics comprise a Full Authority Digital Engine Control (FADEC).

6. The FMU of claim 5, wherein the FMU is contained within a single housing.

7. The FMU of claim 5, wherein the FMU further comprises a cooling device in thermal contact with the FADEC.

8. A full authority digital engine controller (FADEC) for controlling an engine attached to an airframe, the FADEC comprising:

an electronic engine controller (EEC); and

an analog-to-digital circuit connected to a plurality of airframe sensors to convert airframe sensor signals to airframe sensor digital data;

wherein at least a portion of the FADEC is housed within a fuel metering unit (FMU) attached to the engine.

9. The FADEC of claim 8, wherein the portion of the FADEC housed within the FMU is in thermal contact with a cooling device.

10. The FADEC of claim 8, wherein the EEC is connected to an engine sensor to receive an engine sensor signal.

11. The FADEC of claim 10, wherein the EEC produces a control signal, the control signal responsive to the engine sensor signal and the airframe sensor digital data.

12. A system for controlling an aircraft engine attached to an airframe, the system comprising:

a plurality of airframe sensors attached to the airframe to produce airframe sensor signals;

an airframe data concentrator (ADC) attached to the airframe and electrically connected to the plurality of airframe sensors to convert the airframe sensor signals to airframe sensor digital data;

a fuel metering unit (FMU) attached to the engine, the FMU comprising;

an effector; and

an electronic engine controller (EEC);

an engine sensor;

a digital bus connecting the ADC to the EEC;

wherein the engine sensor is electrically connected to the EEC to provide an engine sensor signal to the EEC;

the effector is electrically connected to the EEC to adjust one of a rate of fuel flowing into the engine, a stator vane position, and a rate of bleed air flowing from an engine compressor in response to a control signal sent from the EEC; and

the control signal sent from the EEC is responsive to the airframe sensor digital data sent by the ADC over the digital bus and the engine sensor signal.

13. The system of claim 12, wherein the FMU is contained within a single housing.

14. The system of claim 12, wherein the FMU further comprises a cooling device in thermal contact with the EEC.

15. The system of claim 12, comprising a cockpit display connected to the ADC for displaying engine sensor digital data, wherein the EEC converts the engine sensor signal to the engine sensor digital data and sends the engine sensor digital data to the ADC over the digital bus.

16. The system of claim 12, wherein the engine sensor comprises at least one of a pressure sensor, a temperature sensor, a position sensor, and a rotational speed sensor.

17. The system of claim 12, wherein the effector comprises at least one of a solenoid valve, a stepper motor, a torque motor, and an electric motor.

18. The system of claim 12, wherein the plurality of airframe sensors comprise at least one of a pressure sensor, a temperature sensor, a position sensor, and a rotational speed sensor.

19. A method of controlling an aircraft engine attached to an airframe, the method comprising:

receiving airframe sensor signals from airframe sensors at an airframe data concentrator (ADC) attached to the airframe;

converting the received airframe sensor signals into airframe sensor digital data within the ADC;

transmitting the airframe sensor digital data from the ADC over a digital bus to an electronic engine control (EEC) contained within a fuel metering unit (FMU);

receiving an engine sensor signal from an engine sensor at the EEC;

generating a control signal within the EEC, wherein the generated control signal is responsive to the received airframe sensor digital data and the received engine sensor signal;

transmitting the generated control signal to an effector contained within the FMU; and

adjusting the effector in response to the transmitted control signal to control one of a rate of fuel flowing into the engine, a stator vane position, and a rate of bleed air flowing from an engine compressor.

20. The method of claim 19, further comprising:

converting the received engine sensor signal into engine sensor digital data within the EEC;

transmitting the engine sensor digital data from the EEC over the digital bus to the ADC; and

transmitting the engine sensor digital data from the ADC to a cockpit display.