Engine surge prevention system

Claim 2

A surge control system for a fan jet engine for powering aircraft, said aircraft having independent means for detecting aircraft stall, said engine having a fuel control, including compressor speed control means, for controlling the thrust generated by said engine, said compressor having means, including a bleed valve and actuator therefor, for bleeding air from said compressor, a fan discharge duct housing said fan, the surge control system including at least a pair of total pressure probes circumferentially spaced and mounted in said duct and disposed so that one of said three pair of total pressure probes is in a predetermined location that is insensitive to pressure changes occasioned by a condition of said engine going into surge and the other total pressure probe is sensitive to pressure changes in said duct occasioned by said engine going into surge, computing means responsive to said pair of total pressure probes for producing a signal indicative of an imminent surge condition, means responsive to said signal for opening said bleed valve and simultaneously resetting said compressor speed control means to increase the thrust being generated by said engine.

Claim 3

A surge control system as in claim 1 wherein said aircraft has a source of electricity, and said means responsive to said signal being an electrically conducting switch, said switch being closed upon said computing means produces a signal indicative of a predetermined pressure differential value.

Claim 4

A surge control system as is claim 2 including anti-icing means for preventing ice from forming the total pressure probe so as to falsify the value of the pressure in said duct being sensed.

Claim 5

A surge control as in claim 3 wherein said antiicing means includes concentric tubes surrounding said total pressure probes interconnecting said compressor for flowing compressor bleed air adjacent said total pressure probes.

Claim 6

A surge control system as in claim 3 wherein said means responsive to said signal includes a mechanical connection attached to said bleed valve and another electrical switch whereby said other switch closes the circuit when closed by said mechanical connection for resetting said compressor speed control means.

Claim 7

A surge control system as in claim 5 including means responsive to said independent means for detecting aircraft stall, to conduct current to said switch solely when said stall responsive means is in the inoperative mode.

Claim 8

A surge control system as in claim 6 including means responsive to engine operating parameters for rendering said means for resetting said speed control means inoperative.

Claim 9

A surge control system as in claim 7 wherein said engine operating parameter is indicative of engine thrust reversing.

Claim 10

A surge control system for a fan jet engine for powering aircraft, said aircraft having a source of electricity and independent means for detecting aircraft stall, said engine having a fuel control including compressor speed control means for controlling the thrust generated by said engine, said compressor having means, including a bleed valve and actuator therefor, for bleeding air from said compressor, a fan discharge duct housing said fan, support means supporting said duct adjacent the discharge end of said fan circumferentially spaced in said duct, the surge control system including three total pressure probes circumferentially spaced and mounted in said duct and disposed where one of said three total pressure probes is in a predetermined location that is insensitive to pressure changes occasioned by a condition of said engine going into surge and the other two total pressure probes are located so as to be sensitive to pressure changes in said duct occasioned by said engine going into surge, computing means responsive to said three total pressure probes for producing at least one signal indicative of an imminent surge condition, first means responsive to said signal for opening said bleed valve and second means responsive to said first means for simultaneously resetting said compressor speed control means to increase the thrust being generated by said engine.

Claim 11

A surge control system for a fan jet engine for powering aircraft, said aircraft having a source of electricity and independent means for detecting aircraft stall, said engine having a fuel control including compressor speed control means for controlling the thrust generated by said engine, said compressor having means, including a bleed valve and actuator therefor, for bleeding air from said compressor, a fan discharge duct housing said fan, support means supporting said duct adjacent the discharge end of said fan circumferentially spaced in said duct, the surge control system including three total pressure probes circumferentially spaced and mounted in said duct and disposed where one of said three total pressure probes is in a predetermined location that is insensitive to pressure changes occasioned by a condition of said engine going into surge and the other two total pressure probes are located so as to be sensitive to pressure changes in said duct occasioned by said engine going into surge, computing means responsive to said three total pressure probes for producing at least one signal indicative of an imminent surge condition, first means responsive to said signal for opening said bleed valve and second means responsive to said first means for simultaneously resetting said compressor speed control means to increase the thrust being generated by said engine.

Claim 12

A surge control system as in claim 9 wherein the pressure measured by said one of said three total pressure probes is compared with the pressure measured by each of said other two total pressure probes.

Claim 13

A surge control system as in claim 10 wherein each of said total pressure probes are mounted on said support means.

Claim 14

A surge control system as in claim 11 including concentric tube means surround each of said total pressure probes connected to said compressor for passing compressor bleed air over said total pressure probes to prevent ice from accumulating therein.

Claim 15

A surge control system as in claim 12 including an electrical circuit having switches responsive to said computing means for conducting current to said means responsive to said signal solely when said independent means for detecting aircraft stall is in the inoperative mode.

Claim 16

A surge control system as in claim 13 including means responsive to engine operating parameters for rendering said means for resetting said compressor speed control means inoperative.