US 4,137,708 AGranted

Jet propulsion

AssigneeGeneral Motors Corporation

InventorsRobert H. Aspinwall, Charles R. Baker

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Abstract

A jet propulsion engine and a method of operating a jet propulsion engine for propulsion of an aircraft over a wide range of speed from zero to supersonic. The engine is a turbofan type with a duct burner and with separate variable exhausts from the duct burner and from the gas turbine engine. The gas turbine core engine includes a gas generator and a low pressure turbine which drives the fan. The fan includes variable outlet guide vanes and the low pressure turbine includes a variable first-stage nozzle. The engine is operated as a normal duct burning by-pass jet engine from zero air speed up to about Mach 3. The fuel to the core engine is shut off through a transition range of speeds. Above this range the engine operates with only the duct burner supplied with fuel, with the gas generator windmilling, and with the low pressure turbine continuing to drive the fan to supercharge the duct burner, which operates as a supercharged ramjet.

Claims2

Dependent claims

A method of operating a jet propulsion engine over a wide range of forward speed, the engine including an inlet duct having a forward fan therein with variable flow guide vanes, a fan duct downstream of the inlet duct including a burner, a core gas generator engine downstream of the inlet duct, the core gas generator engine including a high pressure turbine, a variable nozzle and fan turbine coupled to the fan and being energized from the core engine, and first and second variable jet nozzles supplied respectively from the fan duct and the fan turbine, the method comprising:

supplying fuel through the core engine and duct burner for operation as a normal duct-burning bypass engine from zero forward speed up to a supersonic value of forward speed;
progressively reducing core engine fuel following attainment of the supersonic value of forward speed to a fuel cut off point at a supersonic transition forward speed;
and at speeds above the supersonic transition forward speed supplying predetermined ram heated and pressurized air from the inlet duct to the core engine;
controlling the variable flow guide vanes to reduce flow to the core engine;
adjusting the variable flow guide vanes to reduce flow of the predetermined ram heated and pressurized air;
adjusting the variable nozzle to control the expansion ratio of the reduced flow as it passes across the high pressure turbine to produce a regulated extraction of energy from the reduced flow to produce a controlled auxiliary power output from the core gas generator engine;
concurrently opening the second variable jet nozzle to increase the expansion ratio across the fan turbine as ram heated and pressurized air flows through the core engine to extract energy therefrom to drive the fan to supercharge the duct burner during a range of forward speed higher than the transition value, and supplying fuel to the fan duct burner at speeds in excess of the transition value and controlling the first variable jet nozzle to be more opened.

4 more elements

A jet propulsion engine comprising, in combination, a forward fan including a rotor and variable guide vanes;

a core engine including in flow series a compressor supplied with air from the fan, combustion apparatus, and a high pressure turbine connected to drive the compressor;
a low pressure turbine supplied with motive fluid from the high pressure turbine, the low pressure turbine including a variable first stage nozzle and a rotor;
means mechanically coupling the fan rotor to the low pressure turbine rotor;
an exhaust duct from the low pressure turbine including a variable jet nozzle;
a by-pass duct supplied by the fan;
a fuel burner in the duct;
and a variable jet nozzle at the outlet of the by-pass duct;
said variable guide means and said variable first stage nozzle having a first operating position to define a relatively open area for air flow from the forward fan into the by-pass duct and the core engine and to maintain a first predetermined flow of motive fluid from the high pressure to the low pressure turbine so that under low ram conditions of air entering into the fan and with fuel supplied to the combustion apparatus and duct burner the engine operates with the turbines driving the compressor and fan, respectively, as a normal duct-burning turbofan engine;
said variable jet nozzle from the low pressure turbine and said variable jet nozzle at the outlet of the by-pass duct having a first operative position during the normal duct-burning turbofan operation to restrict the air flow from the low pressure turbine and to restrict flow from the fan duct;
means for eliminating fuel flow to the core engine and to continue fuel flow to the duct burner under high ram conditions of entry into the fan at high forward speeds of the engine;
said variable guide means and said variable first stage nozzle having a second operating position during high ram conditions of air entry into the fan to reduce the expansion ratio across the high pressure turbine during high ram conditions of air entry into the fan wherein air is heated to produce extraction of energy from air flow through the high pressure turbine so as to maintain drive of the compressor at a reduced speed when fuel is supplied only to the duct burner;
said variable jet nozzle from the low pressure turbine being controlled to open under high ram conditions of air entry into the fan to increase the expansion ratio across the low pressure turbine during high ram air flow into the core engine to extract energy from ram heated air passing to the core engine to cause the low pressure turbine to drive the fan to supercharge the core engine and duct burner during high ram conditions of air entry into the fan.

9 more elements

Dependencies are inferred from the claim text.