Enhancing engine performance to improve fuel consumption based on atmospheric ice particles

Patent metadata

Field	Value
Publication number	US-10106267-B2
Application number	US-201514927788-A
Country	US
Kind code	B2
Filing date	Oct 30, 2015
Priority date	Oct 30, 2015
Publication date	Oct 23, 2018
Grant date	Oct 23, 2018

Abstract

Systems and methods for enhancing engine performance based on atmospheric ice particles are provided. For example, a method can include selecting one or more points along a flight path of an aircraft and receiving a reflectivity measurement for each of the one or more points obtained using a device located on the aircraft. The method can further include determining an estimate of ice water content for each of the one or more points based at least in part on the reflectivity measurements; and controlling at least one component of the aircraft engine (e.g., a variable bleed valve) based at least in part on the estimate of ice water content for at least one of the plurality of points.

First claim

What is claimed is:

1. A method of controlling an aircraft engine, comprising:
identifying, by one or more processors, one or more points along a flight path of an aircraft;
accessing, by the one or more processors, reflectivity measurements for each of the one or more points, the reflectivity measurements obtained using a radar on the aircraft;
determining, by the one or more processors, a set of estimated ice water content values for each of the one or more points as the aircraft travels along the flight path, each of the estimated values being a correlation of an instance of the reflectivity measurements for the point and an ambient temperature measurement with the point obtained via a sensor;
determining, by the one or more processors, an estimate of ice water content for each of the one or more points by applying a weighted averaging function to the set of estimated ice water content values, wherein the applying assigns a greater weight to the values correlated with the instances of reflectivity measurements obtained for the points closer to the aircraft; and
controlling, by the one or more processors, at least one component of the aircraft engine based at least in part on the estimate of ice water content for the one or more points.

2. The method of claim 1 , wherein the at least one component comprises a variable bleed valve associated with the aircraft engine.

3. The method of claim 1 , wherein the reflectivity measurement for each of the one or more points comprises a radar reflectivity measurement obtained from a radar device.

4. The method of claim 1 , wherein the estimate of ice water content is determined based on the reflectivity measurement using an ice water content estimation algorithm, the ice water content estimation algorithm comprising:
accessing, by the one or more processors, a model correlating ice water content with reflectivity measurements and ambient temperature; and
determining, by the one or more processors, the estimate of ice water content based at least in part on the model.

5. The method of claim 1 , wherein controlling, by the one or more processors, at least one component of the aircraft engine based at least in part on the estimate of ice water content is performed when the aircraft is operating in an ice water content detection mode.

6. The method of claim 5 , wherein the method comprises:
activating, by the one or more computing devices, the ice water content detection mode based at least in part on the ambient temperature.

7. A system for controlling an aircraft engine of an aircraft, comprising:
a radar device located on the aircraft;
a control system comprising one or more processors and one or more memory devices, the one or more memory devices storing computer-readable instructions that when executed by the one or more processors cause the one or more processors to perform operations, the operations comprising:
selecting a plurality of points along a flight path of the aircraft within a beam width of the radar;
accessing radar reflectivity measurements for each of the plurality of points via the radar device;
determining an initial set of estimated ice water content values for each of the plurality of points as the aircraft travels along the flight path, each of the estimated values being a correlation of an instance of the reflectivity measurements for the point and an ambient temperature associated with the point obtained via a sensor;
determining an estimate of ice water content for each of the plurality of points by applying a weighted averaging function to the set of estimated ice water content values, wherein the applying assigns a greater weight to the values correlated with the instances of reflectivity measurements obtained for the points closer to the aircraft; and
controlling at least one component of the aircraft engine based at least in part on the estimate of ice water content for at least one of the plurality of points.

8. The system of claim 7 , wherein the at least one component comprises a variable bleed valve associated with the aircraft engine.

9. The system of claim 7 , wherein the estimate of ice water content is determined based on the radar reflectivity measurement using an ice water content estimation algorithm, the ice water content estimation algorithm comprising:
accessing a model correlating ice water content with radar reflectivity measurements and ambient temperature; and
determining the estimate of ice water content based at least in part the model.

10. The system of claim 7 , the control system is configured to control the at least one component of the aircraft engine based at least in part on the estimate of ice water content when the control system is operating in an ice water content detection mode, wherein the control system is configured to trigger operation in the ice water content detection mode based at least in part on an ambient temperature measurement.

11. An aircraft, comprising:
an aircraft engine comprising one or more variable bleed valves;
a radar device located on the aircraft;
a control system comprising one or more processors and one or more memory devices, the one or more memory devices storing computer-readable instructions that when executed by the one or more processors cause the one or more processors to perform operations, the operations comprising:
selecting a set of points along a flight path of the aircraft;
receiving radar reflectivity measurements for each point in the set of points;
determining a first set of estimated ice water content values for each point in the set of points as the aircraft travels along the flight path, each of the estimated values being a correlation of an instance of in the each first set of estimated ice water content values is associated with the reflectivity measurements for the point and an ambient temperature measurement with the point obtained via a sensor;
determining an estimate of ice water content for each point in the set of points by applying a weighted averaging function to the set of estimated ice water content values, wherein the applying assigns a greater weight to the values correlated with the instances of reflectivity measurements obtained for the points closer to the aircraft; and
controlling at least one component of the aircraft engine based at least in part on the estimate of ice water content for at least one of the plurality of points.

12. The aircraft of claim 11 , wherein the at least one component comprises the one or more variable bleed valves associated with the aircraft engine.

13. The aircraft of claim 11 , wherein the estimate of ice water content is determined based on the radar reflectivity measurement using an ice water content estimation algorithm, the ice water content estimation algorithm comprising:
accessing a model correlating ice water content with radar reflectivity measurements and ambient temperature; and
determining the estimate of ice water content based at least in part the model.

Assignees

• Ge Aviation Systems Llc

Inventors

• Visser Nicholas
• Adibhatla Sridhar
• Lax David Michael

Classifications

• G01S13/953

  mounted on aircraft · CPC title

• Y02T50/671

  Cross-Sectional Technologies · mapped topic

• F02C9/18 Primary

  by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} · CPC title

• G01S17/95

  for meteorological use · CPC title

• F02C9/28

  Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed (F02C9/30 - F02C9/38, F02C9/44 take precedence) · CPC title