Helicopter cruise fuel conserving engine control

• US 4,488,236 A
• Filed: 04/16/1982
• Issued: 12/11/1984
• Est. Priority Date: 04/16/1982
• Status: Expired due to Term

• Current Assignee: Goodrich Pump & Engine Control Systems, Inc. (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Howlett, James J., Zagranski, Raymond D., Morrison, Terry
• Primary Examiner(s): Chin, Gary
• Assistant Examiner(s): Black, Thomas G.
• Application Number:
  US06/369,302
• Time in Patent Office: 970 Days
• Field of Search: 364/431.01-431.05, 364/442, 364/510, 364/427, 364/428, 244/182, 244/180, 377/21, 73/113-114, 318/583-584
• US Class Current: 701/123
• CPC Class Codes: F02C 9/28 Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed F02C9/30 - F02C9/38, F02C9/44 take precedence
• CPC Class Codes: F05D 2220/329 in helicopters
• CPC Class Codes: F05D 2270/07 to improve fuel economy
• CPC Class Codes: G05D 1/0005 with arrangements to save energy
• CPC Class Codes: G05D 1/0858 specially adapted for vertical take-off of aircraft
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A digital fuel control (53) for a helicopter engine (20) controls fuel flow (52) to the engine in response to a turbine reference speed (62) determined in a normal mode (FIG. 5) to be a rated speed, in a fade-in mode (FIG. 6) to be incremented (117, 120) to an estimated optimum minimum speed (114, 115, 125), in an optimizer mode (FIG. 7) to be incremented (138) in a direction (137) leading to least fuel consumption (135), and in a fade-out mode (FIG. 8) to be incremented (151, 153) back to rated speed (154). The invention provides an engine reference speed which results in minimum fuel consumption during cruise flight.

Claims

1. A control for a helicopter engine having a free turbine for normally driving the helicopter rotors at a rated speed, comprising:

means for providing an actual speed signal indicative of the rotary speed of the free turbine;

a fuel valve means for metering fuel to said engine at a rate determined by a fuel command signal applied thereto; and

a fuel controlling signal processing means connected for response to said actual speed signal, for providing a reference speed signal indicative of desired rotary speed of the free turbine, for providing, in response to said actual speed signal and said reference speed signal, a speed error signal indicative of the difference in turbine speed indicated by said actual speed signal and said reference speed signal, and for providing said fuel command signal to said fuel valve means indicative of a desired fuel flow rate as a function of said speed error signal;

wherein the improvement comprises;

said signal processing means comprising means responsive to said fuel command signal for, iteratively, in a sequence of successive iteration periods of time, summing a large number of samples of the fuel flow rate commanded to said valve means over a commensurate sampling period of time, the sampling period in each iteration period being separated from the sampling period of the next subsequent iteration period by a settling period of an order of magnitude approximating the time period required for the helicopter response to a small change in engine speed to be substantially settled, said number of samples being of an order of magnitude to substantially eliminate the effects of noise in said samples on said summation, for providing a current fuel rate signal indicative of said summation, for providing, near the end of each of said iteration periods, a previous fuel rate signal equal to said current fuel rate signal after comparing the current fuel rate signal provided in the current sampling period with the previous fuel rate signal provided in the next previous sampling period, for providing a reference speed increment signal indicative of a small fraction of the turbine reference speed, said increment signal having a sign indicative of either an increase or a decrease in turbine speed and a magnitude small enough so that perturbations in engine speed will not unduly perturb the engine or the helicopter and large enough so that the change in reference will cause a change in fuel flow provided to the engine under helicopter flight conditions in which the engine fuel requirements indicated by said summation signal can vary as a function of turbine speed, for changing the sign of the increment signal in any of said iteration periods in which the current fuel rate signal exceeds the previous fuel rate signal provided in the next previous sampling period, and for providing, in each iteration period, said reference speed signal as the summation of said reference speed signal with said increment signal so that the reference speed signal is incremented, in successive iteration periods, in the same sense so long as said summation signal decreases but is incremented in a reverse sense in the event that said summation signal increases.

2. A control according to claim 1 wherein said signal processing means comprises means for providing said reference speed increment signal indicative of a significant fraction of one percent of the turbine rated speed.

3. A control according to claim 1 wherein said signal processing means comprises means for providing said summation signal in response to on the order of 300 samples in each of said sampling periods.

4. A control according to claim 1 wherein by said signal processing means comprises means for providing said summation signal in response to samples of the fuel flow rate commanded to said valve means over a sampling period of time on the order of one minute.

5. A control according to claim 1 wherein by said signal processing means comprises means for providing a maximum limit speed signal and a minimum speed limit signal respectively indicative of a range of acceptable speeds above and below which operation of the turbine is undesirable with respect to helicopter performance, for comparing the reference speed signal provided in each of said sampling periods to at least one of said limit signals, and for providing said reference equal to one of said limit signals in the event that incrementing in such sampling period results in a reference signal indicative of a speed outside of said range of acceptable speeds.

6. A control for a helicopter engine having a free turbine for normally driving the helicopter rotors at a rated speed, comprising:

means for providing an actual speed signal indicative of the rotary speed of the free turbine;

a fuel valve means for metering fuel to said engine at a rate determined by a fuel command signal applied thereto; and

a fuel controlling signal processing means connected for response to said actual speed signal, for providing a reference speed signal indicative of desired rotary speed of the free turbine, for providing, in response to said actual speed signal and said reference speed signal, a speed error signal indicative of the difference in turbine speed indicated by said actual speed signal and said reference speed signal, for providing said fuel command signal to said fuel valve means indicative of a desired fuel flow rate as a function of said speed error signal;

wherein the improvement comprises;

said signal processing means comprising means for registering a plurality of flight parameter signals, including an altitude signal indicative of current altitude of the helicopter, a temperature signal indicative of the current temperature of the environment outside of the helicopter, an airspeed signal indicative of the current airspeed of the helicopter, and a weight signal indicative of the current total weight of the helicopter, for providing, in response to all of said flight parameter signals, an optimum speed signal indicative of an estimated optimum free turbine speed for minimum engine fuel requirement for helicopter flight conditions indicated by said flight parameter signals, and for providing a manifestation of whether said speed reference signal indicates a speed which is respectively higher or lower than said estimated optimum free turbine speed.

7. A control according to claim 6 wherein said signal processing means comprises means for providing said reference speed signal in response to said estimated optimum speed signal.

8. A control according to claim 7 wherein said signal processing means comprises means for providing said reference speed signal equal to said estimated optimum speed signal.

9. A control according to claim 6 wherein said signal processing means comprises means for providing said manifestation as a fade-in increment signal having a sign indicative of said speed reference signal indicating a speed higher or lower than said estimated optimum free turbine speed and a magnitude small enough so that changes in said reference speed thereby will not unduly perturb the engine or the helicopter, and for, iteratively, in a succession of fade-in periods, providing said speed reference signal as the summation of the speed reference signal provided in the next previous one of said fade-in periods with said fade-in increment signal in each of said fade-in periods in which said previous reference speed signal differs from said estimated optimum speed signal by more than the magnitude of said increment signal, and, in a final one of said fade-in periods in which said previous reference speed signal does not differ from said estimated optimum speed signal by more than said magnitude, providing said reference speed signal equal to said estimated optimum speed signal.

10. A control according to claim 9 wherein by said signal processing means comprises means for providing a fade-in complete control signal indicative of said reference speed signal being provided equal to said estimated optimum speed signal in said final fade-in period, and thereafter, in response to the presence of said fade-in complete control signal, for iteratively, in successive ones of sequence of sampling periods of time, summing, in response to fuel command signal, a large number of samples of the fuel flow rate commanded to said valve means over a commensurate sampling period of time, and for providing a current fuel rate signal indicative of said summation, for providing near the end of each of said sampling periods, a previous fuel rate signal equal to said current fuel rate signal after comparing the current rate signal provided in the current sampling period with the previous fuel rate signal provided in the next previous sampling period, for providing a reference speed increment signal indicative of a small fraction of the turbine reference speed, said increment signal having a sign indicative of either an increase or a decrease in turbine speed, for changing the sign of said increment signal in any of said sampling periods in which the current fuel rate signal exceeds the previous fuel rate signal provided in the next previous sampling period, and for providing, in each of said sampling periods, said reference speed signal as the summation of said reference speed signal with said increment signal so that the reference speed signal is incremented, in successive sampling periods, in the same sense so long as said summation signal decreases but is incremented in a reverse sense in response to said summation signal increasing.