US3566900A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Fuel control system and viscosity sensor used therewith
Assignee: Avco Corp
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Filing: 1969-03-03
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Granted: 1971-03-02
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Expires: 1989-03-03
Abstract
Abstract The disclosure illustrates a fuel viscosity sensor incorporated in a fuel control system for a gas turbine engine to assure a constant engine power output irrespective of fuel viscosity changes. The viscosity sensor comprises a proportional fluidic amplifier having a laminar flow element, series connected with one control jet. The fluidic amplifier is connected to the pressurized fuel supply and its output is proportional to the fuel viscosity. The pressure output from this amplifier is used to correct a flow-metering device for viscosity changes.
Inventors
- 👤 Jay I Black
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-29 21:26
CPC Classifications
F; F15; F15C; F15C1/00; F15C1/002; Y; Y10; Y10S; Y10S261/00; Y10S261/69; Y10T; Y10T137/00; Y10T137/206; Y10T137/2229; Y10T137/2256; Y10T137/2278; Y10T137/2322
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
255 words
In a gas turbine engine having a power output proportional to the rate of flow of fuel supplied to the engine and including: means for pressurizing a source of fuel; means for providing a flow path from the fuel pressurizing means to said engine; a fuel metering orifice interposed in said flow path and having a variable area for varying the fuel flow rate to said engine and the power output thereof; means for maintaining a constant predetermined pressure differential across the orifice, whereby fuel flow through said fuel metering orifice is proportional to the area thereof; the improvement comprising: a fluidic device comprising a nozzle and a means for connecting said nozzle to said fuel flow path means whereby a power stream is discharged from said nozzle, receiver means positioned so that said power stream impinges on said receiver means, and a control jet means connected to said fuel flow path means and adapted to deflect said power stream responsive to flow through said control jet means, said control jet means including a means responsive to at least the viscosity parameter of said fuel for varying the flow through said control jet means; and means connected to said receiver means and responsive to the pressure output of said fluidic device for compensating said pressure differential means to vary the predetermined pressure differential across said orifice; whereby the power output of said engine is maintained at a level proportional to the area of said fuel metering orifice irrespective of the variation in said fuel parameter.
Claim 2
Dependent Claim
255 words
In a gas turbine engine having a power output proportional to the rate of flow of fuel supplied to the engine and including: means for pressurizing a source of fuel; means for providing a flow path from the fuel pressurizing means to said engine; a fuel metering orifice interposed in said flow path and having a variable area for varying the fuel flow rate to said engine and the power output thereof; means for maintaining a constant predetermined pressure differential across the orifice, whereby fuel flow through said fuel metering orifice is proportional to the area thereof; the improvement comprising: a fluidic device comprising a nozzle and a means for connecting said nozzle to said fuel flow path means whereby a power stream is discharged from said nozzle, receiver means positioned so that said power stream impinges on said receiver means, and a control jet means connected to said fuel flow path means and adapted to deflect said power stream responsive to flow through said control jet means, said control jet means including a means responsive to at least the viscosity parameter of said fuel for varying the flow through said control jet means; and means connected to said receiver means and responsive to the pressure output of said fluidic device for compensating said pressure differential means to vary the predetermined pressure differential across said orifice; whereby the power output of said engine is maintained at a level proportional to the area of said fuel metering orifice irrespective of the variation in said fuel parameter.
Claim 3
Dependent Claim
40 words
Apparatus as in claim 1 wherein the flow-varying means of said fluidic device comprises a laminar flow element through which said fuel is passed whereby fuel flow from said control jet means is proportional to the viscosity of said fuel.
Claim 4
Dependent Claim
96 words
Apparatus as in claim 1 wherein: the control jet means of said fluidic device comprises a pair of control jet discharge ports on opposite sides of said power stream and means for forming flow paths from said ports to said fuel flow path means so that the power jet is deflected as a function of the relative flow from said control jet discharge ports; said flow-varying means comprises a laminar flow element interposed in one of said control jet flow paths whereby the power stream is deflected in response to changes in viscosity of said fuel.
Claim 5
Dependent Claim
24 words
Apparatus as in claim 3 wherein said flow-varying means further comprises a sharp-edged orifice interposed in the other of said control jet flow paths.
Claim 6
Dependent Claim
35 words
Apparatus as in claim 4 wherein said sharp-edged orifice has an adjustable variable area whereby the power stream from said fluidic device may be set in an undeflected position for a given level of viscosity.
Claim 7
Dependent Claim
185 words
Apparatus as in claim 5 wherein said means for maintaining a constant predetermined pressure differential across said fuel metering orifice comprises: means for providing a bypass flow path from said fuel flow path means upstream of said fuel metering orifice to a low pressure discharge point; a valve element interposed in said flow path for varying the bypass flow as a function of the displacemEnt of said valve element; means for applying the fuel flow path pressure upstream of said fuel metering orifice to one face of said valve element whereby the valve element is urged in a direction to increase bypass flow; means for applying the fuel flow path pressure downstream from said fuel metering orifice to the opposite face of said valve element; means for yieldably urging said opposite face of the valve element with a predetermined force whereby the valve element controls the bypass flow to maintain said predetermined pressure level across the fuel metering orifice; said compensating means comprises a means responsive to said received pressure for varying the predetermined force which said yieldable urging means exerts on said valve element.
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) | 1974-03-01 | 1974-08-31 | 1975-03-02 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-03-01 | 1978-08-31 | 1979-03-02 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-03-01 | 1982-08-31 | 1983-03-02 | $7700.00 | Window Closed / Lapsed |