Turbine engine power optimization control system

Claim 2

A turbine engine power management and control system for limiting the maximum speed of rotation of a turbine engine, wherein the maximum permissible speed is a function of temperature, and pressure among other factors, comprising: means for sensing the air pressure in the vicinity of the jet engine; means for sensing the temperature in the vicinity of the jet engine; means for measuring the speed of rotation of at least one section of said engine; first and second system means for determining at least two distinctly different respective "Maps" relating maximum jet engine rotational speed to pressure and temperature, each said system means including: (a) circuit means for determining a maximum allowable rotational speed which increases with increasing temperature at lower temperature ranges; (b) means for increasing the maximum allowable rotational speed with increasing altitude and reduced pressure; (c) means for reducing the maximum allowable speed with increasing temperature at higher temperature levels; and (d) means for limiting the allowable speed to a predetermined maximum absolute limit, regardless of temperature and pressure; to thereby determine a composite maximum allowable speed; manually operable switching means for selecting one of said two distinctly different "Maps" of maximum allowable rotational speeds; and means for comparing the actual turbine speed of rotation with the selected composite maximum allowable speed and for limiting the actual speed to the vicinity of said selected maximum allowable speed.

Claim 3

A turbine engine power management and control system as defined in claim 1 further comprising timing means for automatically shifting from one of said "Maps" to another to limit power levels, after a predetermined period of time, whereby the jet engine is protected against excessive stress by prolonged operation at high power levels.

Claim 4

A turbine engine power management and control system for turbine powered aircraft including de-icing equipment, as defined in claim 1, further comprising means for further limiting the maximum speed of rotation of said turbine engines when the aircraft de-icing equipment is turned on.

Claim 5

A turbine engine power management and control system for turbine powered aircraft as defined in claim 1 wherein said manually operable switching means is a set of selectable switches mounted on the pilot handwheel of said aircraft.

Claim 6

A turbine engine power management and control system as defined in claim 4 further including indicator lights associated with each switch for indicating the mode of energization of said system.

Claim 7

A turbine engine power management and control system as defined in claim 4 wherein said switches include individual manually operable selection switches at least for (1) take-off, (2) performance climb, (3) cruise, and (4) approach, power levels.

Claim 8

A turbine engine power management and control system as defined in claim 1 wherein said system includes at least three of said "Maps" involving maximum allowable turbine engine rotational speed.

Claim 9

A turbine engine power management and control system as defined in claim 4 wherein means are provided for limiting the maximum allowed rotational speed of the turbine engines to a speed below that indicated by any of said "Maps" when selected pushbuttons are activated.

Claim 10

A turbine engine power management and control system for fan-jet engines are defined in claim 1, and wherein said system includes means for controlling the speed of the fan section of said turbine engine.

Claim 11

A turbine engine power management and control system for multiple engine aircraft as defined in claim 1, wherein separate means are provided for sensing the speed of rotation of each engine, and for separately limiting the speed of rotation of each engine.

Claim 12

A turbine engine power management and control system for limiting the maximum speed of rotation of a turbine engine, wherein the maximum permissible speed is a function of temperature, and pressure among other factors, comprising: means for sensing the air pressure in the vicinity of the jet engine; means for sensing the temperature in the vicinity of the jet engine; means for measuring the speed of rotation of at least one section of said engine; first and second system means for determining at least two distinctly different respective "Maps" relating maximum jet engine rotational speed to pressure and temperature, each said system means including: (a) circuit means for determining a maximum allowable rotational speed which increases with increasing temperature at lower temperature ranges; (b) means for increasing the maximum allowable rotational speed with increasing altitude and reduced pressure; (c) means for reducing the maximum allowable speed with increasing temperature at higher temperature levels; and (d) means for limiting the allowable speed to a predetermined maximum absolute limit, regardless of temperature and pressure; to thereby determine a composite maximum allowable speed; manually operable switching means for selecting one of said two distinctly different "Maps" of maximum allowable rotational speeds; means for comparing the actual turbine speed of rotation with the selected composite maximum allowable speed and for limiting the actual speed to the vicinity of said selected maximum allowable speed; and timing means for automatically shifting from one of said "Maps" to another to limit power levels, after a predetermined period of time, whereby the jet engine is protected against excessive stress by prolonged operation at high power levels.

Claim 13

A turbine engine power management and control system for limiting the maximum speed of rotation of a turbine engine, wherein the maximum permissible speed is a function of temperature, and pressure among other factors, comprising: means for sensing the air pressure in the vicinity of the jet engine; means for sensing the temperature in the vicinity of the jet engine; means for measuring the speed of rotation of at least one section of said engine; first and second system means for determining at least two distinctly different respective "Maps" relating maximum jet engine rotational speed to pressure and temperature, each said system means including: (a) circuit means for determining a maximum allowable rotational speed which increases with increasing temperature at lower temperature ranges; (b) means for increasing the maximum allowable rotational speed with increasing altitude and reduced pressure; (c) means for reducing the maximum allowable speed with increasing temperature at higher temperature levels; and (d) means for limiting the allowable speed to a predetermined maximum absolute limit, regardless of temperature and pressure; to thereby determine a composite maximum allowable speed; manually operable switching means for selecting one of said two distinctly different "Maps" of maximum allowable rotational speeds; means for comparing the actual turbine speed of rotation with the selected composite maximum allowable speed and for limiting the actual speed to the vicinity of said selected maximum allowable speed; and timing means for automatically shifting from one of said "Maps" to another to limit power levels, after a predetermined period of time, whereby the jet engine is protected against excessive stress by prolonged operation at high power levels.

Claim 14

A turbine engine power management and control system for limiting the maximum speed of rotation of an aircraft turbine engine, wherein the maximum permissible speed is a function of temperature, and pressure among other factors, comprising: means for sensing the air pressure in the vicinity of the jet engine; means for sensing the temperature in the vicinity of the jet engine; means for measuring the speed of rotation of at least one section of said engine; first and second system means for determining at least two distinctly different respective "Maps" relating maximum jet engine rotational speed to pressure and temperature, each said system means including: (a) circuit means for determining a maximum allowable rotational speed which increases with increasing temperature at lower temperature ranges; (b) means for increasing the maximum allowable rotational speed with increasing altitude and reduced pressure; (c) means for reducing the maximum allowable speed with increasing temperature at higher temperature levels; and (d) means for limiting the allowable speed to a predetermined maximum absolute limit, regardless of temperature and pressure; to thereby determine a composite maximum allowable speed; manually operable switching means for selecting one of said two distinctly different "Maps" of maximum allowable rotational speeds, said manually operable switching means comprising pushbutton switches mounted on the pilot handwheel of the aircraft; and means for comparing the actual turbine speed of rotation with the selected composite maximum allowable speed and for limiting the actual speed to the vicinity of said selected maximum allowable speed.

Claim 15

A turbine engine power management and control system for limiting the maximum speed of rotation of an aircraft turbine engine, wherein the maximum permissible speed is a function of temperature, and pressure among other factors, comprising: means for sensing the air pressure in the vicinity of the jet engine; means for sensing the temperature in the vicinity of the jet engine; means for measuring the speed of rotation of at least one section of said engine; first and second system means for determining at least two distinctly different respective "Maps" relating maximum jet engine rotational speed to pressure and temperature, each said system means including: (a) circuit means for determining a maximum allowable rotational speed which increases with increasing temperature at lower temperature ranges; (b) means for increasing the maximum allowable rotational speed with increasing altitude and reduced pressure; (c) means for reducing the maximum allowable speed with increasing temperature at higher temperature levels; and (d) means for limiting the allowable speed to a predetermined maximum absolute limit, regardless of temperature and pressure; to thereby determine a composite maximum allowable speed; manually operable switching means for selecting one of said two distinctly different "Maps" of maximum allowable rotational speeds, said manually operable switching means comprising pushbutton switches mounted on the pilot handwheel of the aircraft; and means for comparing the actual turbine speed of rotation with the selected composite maximum allowable speed and for limiting the actual speed to the vicinity of said selected maximum allowable speed.

Claim 16

A turbine engine power management and control system for limiting the maximum speed of rotation of an aircraft turbine engine, wherein the maximum permissible speed is a function of temperature, and pressure among other factors, comprising: means for sensing the air pressure in the vicinity of the jet engine; means for sensing the temperature in the vicinity of the jet engine; means for measuring the speed of rotation of at least one section of said engine; first and second system means for determining at least two distinctly different respective "Maps" relating maximum jet engine rotational speed to pressure and temperature, each said system means including: (a) circuit means for determining a maximum allowable rotational speed which increases with increasing temperature at lower temperature ranges; (b) means for increasing the maximum allowable rotational speed with increasing altitude and reduced pressure; (c) means for reducing the maximum allowable speed with increasing temperature at higher temperature levels; and (d) means for limiting the allowable speed to a predetermined maximum absolute limit, regardless of temperature and pressure; to thereby determine a composite maximum allowable speed; manually operable switching means for selecting one of said two distinctly different "Maps" of maximum allowable rotational speeds, said manually operable switching means comprising pushbutton switches mounted on the pilot handwheel of the aircraft; means for comparing the actual turbine speed of rotation with the selected composite maximum allowable speed and for limiting the actual speed to the vicinity of said selected maximum allowable speed; and timing means for automatically shifting from one of said "Maps" to another to limit power levels, after a predetermined period of time, whereby the jet engine is protected against excessive stress by prolonged operation at high power levels.

Claim 17

A turbine engine power management and control system for limiting the maximum speed of rotation of an aircraft turbine engine, wherein the maximum permissible speed is a function of temperature, and pressure among other factors, comprising: means for sensing the air pressure in the vicinity of the jet engine; means for sensing the temperature in the vicinity of the jet engine; means for measuring the speed of rotation of at least one section of said engine; first and second system means for determining at least two distinctly different respective "Maps" relating maximum jet engine rotational speed to pressure and temperature, each said system means including: (a) circuit means for determining a maximum allowable rotational speed which increases with increasing temperature at lower temperature ranges; (b) means for increasing the maximum allowable rotational speed with increasing altitude and reduced pressure; (c) means for reducing the maximum allowable speed with increasing temperature at higher temperature levels; and (d) means for limiting the allowable speed to a predetermined maximum absolute limit, regardless of temperature and pressure; to thereby determine a composite maximum allowable speed; manually operable switching means for selecting one of said two distinctly different "Maps" of maximum allowable rotational speeds, said manually operable switching means comprising pushbutton switches mounted on the pilot handwheel of the aircraft; means for comparing the actual turbine speed of rotation with the selected composite maximum allowable speed and for limiting the actual speed to the vicinity of said selected maximum allowable speed; and timing means for automatically shifting from one of said "Maps" to another to limit power levels, after a predetermined period of time, whereby the jet engine is protected against excessive stress by prolonged operation at high power levels.

Claim 18

An aircraft turbine engine power management and control system for limiting the power level of a turbine engine, wherein the maximum permissible power level is a function of temperature, and pressure among other factors, comprising: means for sensing the air pressure in the vicinity of the turbine engine; means for sensing the temperature in the vicinity of the turbine engine; means for measuring at least one parameter which is a function of the power level of said engine; first and second system means for determining at least two distinctly different respective "Maps" relating maximum turbine engine power level to pressure and temperature, each said system means including means for limiting the power level parameter to a predetermined maximum absolute limit, regardless of temperature and pressure to thereby determine a composite maximum allowable speed; manually operable switching means for selecting one of said two distinctly different "Maps" of maximum allowable power levels; and means for comparing the actual power level parameter with the selected composite maximum allowable power level and for limiting the turbine engine power level to the vicinity of said selected maximum allowable power level.

Claim 19

An aircraft turbine engine power management and control system for limiting the power level of a turbine engine, wherein the maximum permissible power level is a function of temperature, and pressure among other factors, comprising: means for sensing the air pressure in the vicinity of the turbine engine; means for sensing the temperature in the vicinity of the turbine engine; means for measuring at least one parameter which is a function of the power level of said engine; first and second system means for determining at least two distinctly different respective "Maps" relating maximum turbine engine power level to pressure and temperature, each said system means including means for limiting the power level parameter to a predetermined maximum absolute limit, regardless of temperature and pressure to thereby determine a composite maximum allowable speed; manually operable switching means for selecting one of said two distinctly different "Maps" of maximum allowable power levels; and means for comparing the actual power level parameter with the selected composite maximum allowable power level and for limiting the turbine engine power level to the vicinity of said selected maximum allowable power level.

Claim 20

A turbine engine power management and control system for turbine powered aircraft including special aircraft operating equipment, as defined in claim 14, further comprising means for further limiting the maximum power level of said turbine engines when the aircraft special operating equipment is in operation.

Claim 21

An aircraft turbine engine power management and control system for limiting the power level of a turbine engine, wherein the maximum permissible power level is a function of temperature, and pressure among other factors, comprising: means for sensing the air pressure in the vicinity of the turbine engine; means for sensing the temperature in the vicinity of the turbine engine; means for measuring at least one parameter which is a function of the power level of said engine; first and second system means for determining at least two distinctly different respective "Maps" relating maximum turbine engine power level to pressure and temperature, each said system means including means for limiting the power level parameter to a predetermined maximum absolute limit, regardless of temperature and pressure to thereby determine a composite maximum allowable speed; manually operable switching means for selecting one of said two distinctly different "Maps" of maximum allowable power levels; means for comparing the actual power level parameter with the selected composite maximum allowable power level and for limiting the turbine engine power level to the vicinity of said selected maximum allowable power levels; and timing means for automatically shifting from one of said "Maps" to another to limit power levels, after a predetermined period of time, whereby the jet engine is protected against excessive stress by prolonged operation at high power levels.

Claim 22

An aircraft turbine engine power management and control system for limiting the power level of a turbine engine, wherein the maximum permissible power level is a function of temperature, and pressure among other factors, comprising: means for sensing the air pressure in the vicinity of the turbine engine; means for sensing the temperature in the vicinity of the turbine engine; means for measuring at least one parameter which is a function of the power level of said engine; first and second system means for determining at least two distinctly different respective "Maps" relating maximum turbine engine power level to pressure and temperature, each said system means including means for limiting the power level parameter to a predetermined maximum absolute limit, regardless of temperature and pressure to thereby determine a composite maximum allowable speed; manually operable switching means for selecting one of said two distinctly different "Maps" of maximum allowable power levels; means for comparing the actual power level parameter with the selected composite maximum allowable power level and for limiting the turbine engine power level to the vicinity of said selected maximum allowable power levels; and timing means for automatically shifting from one of said "Maps" to another to limit power levels, after a predetermined period of time, whereby the jet engine is protected against excessive stress by prolonged operation at high power levels.

Claim 23

A turbine engine power management and control system for turbine powered aircraft including special aircraft operating equipment, as defined in claim 16, further comprising means for further limiting the maximum power level of said turbine engines when the aircraft special operating equipment is in operation.