Patent EP1114991A2 successfully refreshed from Google Patents.
EP1114991A2
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Methods and systems for estimating engine faults
Assignee: General Electric Co
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Filing: 2000-12-15
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Granted: —
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Expires: 2020-12-15
Abstract
Abstract Systems and methods for estimating engine faults are described. In one embodiment, the method includes the steps of obtaining (62) measured engine quantities at a first operating condition, obtaining (64) measured engine quantities at a second operating condition, and generating (66) an estimated fault vector y based on the measured engine quantities obtained at the first and second operating conditions. Model (30)-based values can also be obtained at the first and second operating conditions and used in connection with generating vector y.
Inventors
- 👤 Sridhar Abibhatla
- 👤 Mathew William Wiseman
Bibliographic Details
Application Number
—
Jurisdiction
EP
Data Source
google_patents
Last Synchronized
2026-11-01 21:22
CPC Classifications
G; G01; G01M; G01M15/00; F; F05; F05B; F05B2270/00
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
53 words
A method for estimating engine faults, said method comprising the steps of: obtaining measured engine quantities (14) at a first operating condition; obtaining measured engine quantities (18) at a second operating condition; generating (66) an estimated fault vector y based on the measured engine
quantities obtained at the first and second operating conditions.
Claim 2
Dependent Claim
24 words
A method in accordance with Claim 1 wherein the measured engine
quantities (14, 18) comprise at least one of rotor speed, temperature, and pressure.
Claim 3
Dependent Claim
40 words
A method in accordance with Claim 1 or 2 wherein the first operating
condition and second operating condition each comprise at least one of an idle point,
a takeoff point, a climb point, a cruise point, and a descent point.
Claim 4
Dependent Claim
29 words
A method in accordance with Claim 1 or 2 wherein the first operating
condition occurs during a first flight and the second operating condition occurs
during a subsequent flight.
Claim 5
Dependent Claim
23 words
A method in accordance with Claim 1 or 2 wherein the first operating
condition and second operating condition occur during the same flight.
Claim 6
Dependent Claim
56 words
A processor (12) programmed for estimating engine faults, said processor
programmed to: sample (62) measured engine quantities (14) at a first operating condition; sample (64) measured engine quantities (18) at a second operating
condition; and generate (66) an estimated fault vector y based on the measured engine
quantities obtained at the first and second operating conditions.
Claim 7
Dependent Claim
24 words
A processor in accordance with Claim 6 wherein the sampled engine
quantities (14, 18) comprise at least one of rotor speed, temperature, and pressure.
Claim 8
Dependent Claim
41 words
A processor (12) in accordance with Claim 6 or 7 wherein the first operating
condition and second operating condition each comprise at least one of an idle point,
a takeoff point, a climb point, a cruise point, and a descent point.
Claim 9
Dependent Claim
30 words
A processor (12) in accordance with Claim 6 or 7 wherein the first operating
condition occurs during a first flight and the second operating condition occurs
during a subsequent flight.
Claim 10
Dependent Claim
60 words
A processor (12) programmed for estimating engine faults, said processor
programmed to: sample (62) measured engine quantities (14) at a first operating condition; sample (64) measured engine quantities (18) at a second operating
condition; and generate (66) an estimated fault vector y by implementing a neural network
comprising inputs of sensor and model (30) values and outputs of fault magnitudes.
References Cited (Backward Citations)
No citation records indexed.
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