Propulsion system control

Claim 2

A propulsion and control system comprising gas generator means capable of producing high energy gases; ducting connected to the gas generator means for receiving high energy gases therefrom; at least two thrust units connected with the ducting for converting the high energy gases from the ducting into propulsive thrusts; separate pressure control means associated with each thrust unit, each pressure control means being normally in an open condition wherein a minimum restriction of the flow to the thrust unit with which it is associated exists, each pressure control means being operable independently of the other pressure control means to restrict, but not block, the flow of high energy gases to the associated thrust unit and to effect a back pressure in that portion of the ducting located upstream from the two pressure control means and downstream from the gas generator; and means associated with the gas generator means for causing it to deliver gases at an even higher energy level when either one of the pressure control means is operated to create a back pressure in the ducting, whereby the thrust unit associated with the pressure control means which is not operated will deliver greater thrust than the thrust unit associated with the operated pressure control means which will still continue to deliver thrust.

Claim 3

The structure according to claim 1 wherein the gas generating means comprises at least two gas generators connected to the ducting upstream from the pressure control means; and wherein the discharge portions of the two gas generators are in communication through the ducting so that when one of the pressure control means is operated, the back pressure at both gas generators is increased.

Claim 4

The structure according to claim 1 wherein the pressure control means are in the portions of the ducting leading to the thrust units and throtTle the high energy gases passing through the ducting when they are operated.

Claim 5

The structure according to claim 12 wherein the gas generating means is a turbine engine comprising a compressor for compressing air, a combustion chamber located downstream from the compressor for burning a fuel with the compressed air, and a turbine located downstream from the combustion chamber for receiving gases derived from the combustion chamber, the turbine and compressor including a common rotor.

Claim 6

The structure according to claim 1 wherein the ducting includes a thrust unit duct connected to each thrust unit and a connecting duct interconnecting the thrust unit ducts; wherein the gas generating means includes a turbine engine is connected to each thrust unit duct upstream from the connecting duct; and wherein the pressure control means are located in the thrust unit ducts downstream from the connecting duct.

Claim 7

The structure according to claim 5 wherein each thrust unit duct includes at least two flow channels; wherein the pressure control means includes valves in each channel; and wherein one of the two valves of each thrust unit duct may be moved to a completely closed position in which it completely blocks its channel while the other valve may be independently moved from an open position to positions in which it further restricts the channel in which it is disposed, whereby both thrust units may be utilized with gases supplied from only one gas generating means.

Claim 8

A propulsion system according to claim 1 wherein each thrust unit comprises a free-wheeling fan rotor provided with turbine blades at its periphery, and a scroll connected with the ducting for directing gases discharged therefrom across the turbine blades on the fan rotor.

Claim 9

A propulsion and control system comprising: at least one gas generator capable of converting fuel into high energy gases and having a rotor, the speed of which is affected by the back pressure of the high energy gases with the speed tending to fall off as the back pressure increases, and a fuel control system which is responsive to the rotor speed and tends to keep the rotor speed constant by regulating the flow of fuel to the gas generator; ducting for receiving the high energy gases discharged by the gas generator and including at least two modulating sections and a cross connecting section interconnecting the two modulating sections so that the two modulating sections are in communication, the ducting being connected to the gas generator upstream from the modulating sections such that the gas generator discharges into the ducting as an undivided flow; a thrust unit connected to each modulating section of the ducting for converting the high energy gases from the ducting into propulsive thrusts; a pressure controller in each modulating section for increasing the back pressure of the high energy gases in the cross connecting section of the ducting and at the discharge end of the gas generator when operated, the pressure controllers being operable independently of each other, whereby when one pressure controller is operated, the back pressure at the gas generator will increase and the rotor speed will tend to fall off, whereupon the fuel control system will sense the decrease in speed and deliver more fuel to the gas generator so that it will exhaust gases into the ducting at an even higher energy level, thus enabling both thrust units to deliver thrust with the thrust unit downstream from the pressure controller which is not operated delivering the greater thrust.

Claim 10

A propulsion and control system comprising: at least one gas generator capable of converting fuel into high energy gases and having a rotor, the speed of which is affected by the back pressure of the high energy gases with the speed tending to fall off as the back pressure increases, and a fuel control system which is responsive to the rotor speed and tends to keep the rotor speed constant by regulating the flow of fuel to the gas generator; ducting for receiving the high energy gases discharged by the gas generator and including at least two modulating sections and a cross connecting section interconnecting the two modulating sections so that the two modulating sections are in communication, the ducting being connected to the gas generator upstream from the modulating sections such that the gas generator discharges into the ducting as an undivided flow; a thrust unit connected to each modulating section of the ducting for converting the high energy gases from the ducting into propulsive thrusts; a pressure controller in each modulating section for increasing the back pressure of the high energy gases in the cross connecting section of the ducting and at the discharge end of the gas generator when operated, the pressure controllers being operable independently of each other, whereby when one pressure controller is operated, the back pressure at the gas generator will increase and the rotor speed will tend to fall off, whereupon the fuel control system will sense the decrease in speed and deliver more fuel to the gas generator so that it will exhaust gases into the ducting at an even higher energy level, thus enabling both thrust units to deliver thrust with the thrust unit downstream from the pressure controller which is not operated delivering the greater thrust.

Claim 11

A propulsion and control system according to claim 8 wherein at least two gas generators are provided with one being connected to the ducting immediately upstream from the one modulating duct and the other being connected to the ducting immediately upstream from the other modulating duct; and wherein the cross connecting section communicates with the modulating section downstream from the gas generators and upstream from the pressure controllers.

Claim 14

A method according to claim 10 wherein the gas generating means includes two gas generators which discharge into the ducting at different locations with the one being located closer to one of the thrust units and the other being located closer to the other thrust unit; and further characterized by passing all of the gases discharged from the gas generator located close to the thrust unit which receives the unrestricted flow through that thrust unit, and passing some of the gases from the generator located close to the thrust unit which receives the restricted flow through the thrust unit which receives the unrestricted flow also.