US3935558A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Surge detector for turbine engines
Assignee: RTX Corp
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Filing: 1974-12-11
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Granted: 1976-01-27
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Expires: 1994-12-11
Abstract
Abstract A pair of pressure transducers are connected to pressure probes positioned in a flow passage of a turbofan engine downstream of the fan and respond to pressure fluctuations which occur in the airstream. One transducer has a high response capability, and its output is passed through a band-pass filter to isolate the high frequencies of interest. The other transducer has a low response capability, and its output is passed through a low-pass filter to provide the steady state pressure level. A triggering level is scheduled as a function of the steady state pressure level, and a comparator is used to continuously compare the triggering level with the level of the high frequency pressure signal produced in the band-pass filter. If the amplitude of the high frequency pressure is greater than that of the triggering level, the engine is approaching a surge or stall condition, and a warning signal is generated which may be used to institute corrective action.
Inventors
- 👤 Ronald J. Miller
- 👤 Thomas M. Randolph
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 17:11
CPC Classifications
G; G01; G01L; G01L23/00; G01L23/08; F; F04; F04D; F04D27/00; F04D27/02
Claims Analysis
Total Claims: 12
Claim 1
Independent Claim
123 words
An indicator for a turbine engine comprising pressure sensing means positioned in a flow path of said engine and producing signals which are a function of the gas pressure oscillations therein, a band-pass filter connected to receive said signals and passing therethrough only the high frequency signal components characteristic of engine surge, a low-pass filter also connected to receive said signals and passing therethrough only the low frequency signal components indicative of the steady state pressure, means for producing from said low frequency signal components a triggering signal, and comparator means for comparing said high frequency signal components with said triggering signal and producing an output signal when the amplitude of said high frequency signal components exceeds the amplitudes of said triggering signal.
Claim 2
Dependent Claim
123 words
An indicator for a turbine engine comprising pressure sensing means positioned in a flow path of said engine and producing signals which are a function of the gas pressure oscillations therein, a band-pass filter connected to receive said signals and passing therethrough only the high frequency signal components characteristic of engine surge, a low-pass filter also connected to receive said signals and passing therethrough only the low frequency signal components indicative of the steady state pressure, means for producing from said low frequency signal components a triggering signal, and comparator means for comparing said high frequency signal components with said triggering signal and producing an output signal when the amplitude of said high frequency signal components exceeds the amplitudes of said triggering signal.
Claim 3
Dependent Claim
26 words
An indicator as in claim 1 in which said pressure sensing means comprises a first high response pressure transducer, and a second low response pressure transducer.
Claim 4
Dependent Claim
35 words
An indicator as in claim 2 in which the signals produced by said first transducer are fed to said band-pass filter, and the signals produced by said second transducer are fed to said low-pass filter.
Claim 5
Dependent Claim
28 words
An indicator as in claim 1 in which said band-pass filter is tuned to pass therethrough signal components in the approximate range of 10 Hz to 250 Hz.
Claim 6
Dependent Claim
23 words
An indicator as in claim 1 in which the low frequency signal components passed through said low-pass filter are below about 1 Hz.
Claim 7
Dependent Claim
24 words
An indicator as in claim 1 in which said pressure sensing means is positioned in the fan duct airflow path of a turbofan engine.
Claim 8
Dependent Claim
19 words
An indicator as in claim 1 in which said means for producing a triggering signal is a function generator.
Claim 9
Dependent Claim
55 words
An indicator as in claim 7 in which said function generator produces a triggering signal which is constant at low amplitudes of said low frequency signal components, which increases linearly with intermediate amplitudes of said low frequency signal components, and which is a high constant value at high amplitudes of said low frequency signal components.
Claim 10
Independent Claim
87 words
A method for determining the imminence of surge in a turbojet engine comprising the steps of producing signals indicative of the gas pressure oscillations which occur in a flow path of said engine, modifying said gas pressure oscillation signals by removing therefrom the frequency components which are not characteristic of imminent engine surge, developing from said gas pressure oscillation signals a steady state pressure signal, producing from said steady state pressure signal a triggering signal, and comparing said triggering signal with said modified gas pressure oscillation signals.
Claim 11
Independent Claim
87 words
A method for determining the imminence of surge in a turbojet engine comprising the steps of producing signals indicative of the gas pressure oscillations which occur in a flow path of said engine, modifying said gas pressure oscillation signals by removing therefrom the frequency components which are not characteristic of imminent engine surge, developing from said gas pressure oscillation signals a steady state pressure signal, producing from said steady state pressure signal a triggering signal, and comparing said triggering signal with said modified gas pressure oscillation signals.
Claim 12
Dependent Claim
35 words
A method as in claim 9 and including the step of generating an output signal indicative of the imminence of surge in said engine when said modified gas pressure oscillation signals exceed said triggering signal.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1979-01-26 | 1979-07-28 | 1980-01-27 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1983-01-26 | 1983-07-28 | 1984-01-27 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1987-01-26 | 1987-07-28 | 1988-01-27 | $7700.00 | Window Closed / Lapsed |