Real-time engine inlet barrier filter condition monitor

Patent metadata

Field	Value
Publication number	US-2026084831-A1
Application number	US-202418895620-A
Country	US
Kind code	A1
Filing date	Sep 25, 2024
Priority date	Sep 25, 2024
Publication date	Mar 26, 2026
Grant date	—

Abstract

An aircraft includes a turboshaft engine for powering the aircraft; an inlet barrier filter (IBF) for filtering air at an inlet through which the turboshaft engine draws inlet air; a differential pressure transducer for measuring a differential pressure across the IBF during operation of the aircraft; and a flight control computer system configured to, during operation of the aircraft, periodically calculate a restriction of an airflow through the IBF, periodically determine a rate of change of the restriction of the airflow, compare the rate of change to a threshold rate, and provide an alert to a pilot of the aircraft when the determined rate of change exceeds the threshold rate.

First claim

What is claimed is:

1 . An aircraft comprising:
a turboshaft engine for powering the aircraft; an inlet barrier filter (IBF) for filtering air at an inlet through which the turboshaft engine draws inlet air; a differential pressure transducer for measuring a differential pressure across the IBF during operation of the aircraft; and a flight control computer system configured to, during operation of the aircraft:
periodically calculate a restriction of an airflow through the IBF;
periodically determine a rate of change of the restriction of the airflow;
compare the rate of change to a threshold rate; and
provide an alert to a pilot of the aircraft when the determined rate of change exceeds the threshold rate.

2 . The aircraft of claim 1 , wherein the restriction of the airflow through the IBF is calculated as a function of the differential pressure measured by the differential pressure transducer and at least one characteristic differential pressure value.

3 . The aircraft of claim 1 , further comprising an instrument panel including an indicator configured to provide the alert.

4 . The aircraft of claim 3 , wherein the indicator comprises a gauge.

5 . The aircraft of claim 3 , wherein the indicator comprises a light element.

6 . The aircraft of claim 1 , wherein the flight control computer system is further configured to estimate from the rate of change an amount of time the aircraft can continue to operate in current conditions before the restriction of the airflow reaches a maximum limit.

7 . The aircraft of claim 1 , further comprising an instrument panel including an indicator configured to present a text message including the estimated amount of time.

8 . The aircraft of claim 1 , wherein the aircraft comprises a rotorcraft.

9 . A system for monitoring a condition of an inlet barrier filter (IBF) for filtering air at an inlet through which a turboshaft engine for powering operation of an aircraft draws inlet air, the system comprising:
a differential pressure transducer configured to periodically take a measurement of a differential pressure across the IBF during operation of the aircraft; and a flight control computer system configured to, during operation of the aircraft:
periodically calculate a restriction of an airflow through the IBF;
periodically determine a rate of change of the restriction of the airflow;
compare the rate of change to a threshold rate; and
provide an alert to a pilot of the aircraft when the determined rate of change exceeds the threshold rate.

10 . The system of claim 9 , wherein the restriction of the airflow through the IBF is calculated as a function of the differential pressure measured by the differential pressure transducer and at least one characteristic differential pressure value.

11 . The system of claim 9 , further comprising an indicator within a cockpit of the aircraft, the indicator configured to provide the alert.

12 . The system of claim 11 , wherein the indicator comprises a gauge.

13 . The system of claim 11 , wherein the indicator comprises a light element.

14 . The system of claim 9 , wherein the flight control computer system is further configured to estimate from the rate of change an amount of time the aircraft can continue to operate in current conditions before the restriction of the airflow reaches a maximum limit.

15 . The system of claim 14 , further comprising an indicator within a cockpit of the aircraft, the indicator configured to present a text message including the estimated amount of time.

16 . One or more non-transitory computer-readable storage media comprising instructions for execution that, when executed by a processor, are operable to cause to be performed operations comprising:
periodically calculating a restriction of an airflow through an inlet barrier filter (IBF) for filtering air at an inlet through which a turboshaft engine for powering operation of an aircraft draws inlet air; periodically determining a rate of change of the restriction of the airflow; comparing the rate of change to a threshold rate; and providing an alert to a pilot of the aircraft when the determined rate of change exceeds the threshold rate.

17 . The one or more non-transitory computer-readable storage media of claim 16 , wherein the restriction of the airflow through the IBF is calculated as a function of a differential pressure measured by a differential pressure transducer provided in the aircraft proximate the IBF and at least one characteristic differential pressure value.

18 . The one or more non-transitory computer-readable storage media of claim 16 , wherein the operations further comprise causing the alert to be displayed on an indicator within a cockpit of the aircraft.

19 . The one or more non-transitory computer-readable storage media of claim 18 , wherein the indicator comprises at least one of a gauge or a light element.

20 . The one or more non-transitory computer-readable storage media of claim 16 , wherein the operations further comprise:
estimating from the rate of change an amount of time the aircraft can continue to operate in current conditions before the restriction of the airflow reaches a maximum limit; and causing to be presented on an indicator provided in a cockpit of the aircraft a text message including the estimated amount of time.

Assignees

• Textron Innovations Inc

Inventors

• Parsons Thomas Dewey
• Steinert Alan Hisashi

Classifications

• G01N2015/084

  Testing filters · CPC title

• G01N15/0826

  and measuring fluid flow rate, i.e. permeation rate or pressure change · CPC title

• B64D2045/0085

  Devices for aircraft health monitoring, e.g. monitoring flutter or vibration · CPC title

• F05D2270/3015

  differential pressure · CPC title

• F05D2270/11

  to prolong engine life · CPC title