JPS6067753A - Gas-turbine engine - Google Patents

Abstract

PURPOSE:To perform the afterburning of an engine in a stable manner even when turbine inlet temperature is high and oxygen contained in a combustion gas is little, by installing a device which leads the oxygen for combustion of fuel in an afterburner of the gas-turbine engine. CONSTITUTION:A gas turbine engine 1 is provided with an air intake 2, a compressor 4 installed in front of a rotor 3, a combustor 5, a turbine 6 installed in the rear of the rotor 3, an afterburner 7 and a jet nozzle 8. In the case aforesaid, a flow passage 9 to lead pressure oxygen into the afterburner 7 is additionally installed therein and its one end 9b is set up in a combustion gas flow passage 13 of the afterburner 7. And, a tank 12 storing oxygen under specified pressure is installed in this flow passage 9 with the hlep of a pump 10, an on-off valve 11 and another end part 9a of the flow passage 9 interconnected through. With this constitution, in the case where turbine inlet temperature is high and a quantity of oxygen contained in a combustion gas is small, the oxygen is fed out of the flow passage 9 so that afterburning takes place in a stable manner.

Description

[Detailed description of the invention] The present invention relates to gas turbine engines.

Turbojet engines, turbofan engines, etc. are in practical use as aerospace turbine engines. In this aviation Kasturbine engine, air compressed to ram pressure by two engines is further compressed by a compressor, and this compressed air is led to a combustor to burn fuel and compress the combustion scum of high temperature island pressure. After being expanded by the turbine that drives the aircraft, it is expanded to atmospheric pressure using a jet nozzle to generate a far-reaching jet to provide the aircraft's propulsion force.

In order to increase the thermal efficiency of a gas turbine engine including this aviation gas turbine, it is necessary to increase the temperature of the turbine inlet by I+,'1.

However, the turbine inlet temperature is limited by J'' due to the heat resistance of the turbine blades, and if the turbine blades have a low heat resistance temperature, it is possible to increase the gas +1.1 degrees by mixing dilution air into the combustion scum in the combustor. If the allowable temperature of the turbine blades is sieve, the combustion gas is not diluted, and the combustion in the combustor is performed near the stoichiometric ratio, so that the combustion gas at the smelt temperature is fed to the turbine. .

On the other hand, in aircraft equipped with gas turbine engines,
When it is necessary to temporarily increase thrust during takeoff or when accelerating beyond the speed of sound, 77 taberning is performed for this purpose. This afterburning injects fuel into the combustion gas whose temperature has decreased due to expansion in the turbine.
This fuel is combusted using unburned oxygen contained in the combustion residue to raise the temperature of the combustion gas, and the resulting heated combustion gas is expanded through a jet nozzle to generate strong propulsive force.

However, as mentioned above, in order to improve the thermal efficiency of the gas turbine, the combustion ratio in the combustor approaches the theoretical mixture ratio by increasing the temperature at the lowest temperature, that is, the temperature at the turbine inlet. The amount of unburned oxygen contained in the combustion gas decreases. If the content of oxygen in the combustion residue is low, combustion of the fuel for afterburning becomes unstable, and furthermore, combustion becomes impossible.

The present invention has been made in view of the above-mentioned circumstances, and its purpose is to stably perform afterburning when the turbine/injection temperature is high and the Qf of oxygen contained in the combustion residue is low. The purpose of the present invention is to provide a caster turbine engine that has been improved.

Hereinafter, nine embodiments of the present invention will be explained based on the figures.

Gaster Hiso Engine/1 has air intake port 2. A first compressor 4 provided in front of the rotor 3. A turbine 6 provided behind the combustor 5 rotor 3, an afterburner 7, and
A jet nozzle 8 is provided.

The air flowing in from the air intake port 2 is compressed by the compressor 4 and guided to the combustor 5, where the fuel supplied to the combustor 5 is combusted and the generated sieve part ihj, I:I. The combustion residue expands in the turbine 6 and drives the turbine 6.

The turbine 4 is driven by the turbine 6 via the rotor 3. The combustion scum leaving the turbine 6 expands in the jet nozzle 8 and becomes an associated injection tube to generate 1L propellant.

9 supplies oxygen pressurized to a predetermined pressure to the gas turbine engine 1.
This is a flow path for accessing the afterburner 7. 10 is a pump for pressurizing oxygen and supplying it to the afterbarb 7, and this pump 1o is driven by a motor (not shown) in the SI. 11 is an on-off valve, and this on-off valve 11 and the pump 10
The end 9a of the flow path 9 is in communication with a tank 12 that stores oxygen at a predetermined pressure. The other end 9 of the flow path 9
b is arranged so as to discharge oxygen into the combustion residue flow path 13 of the afterburner 7, or arranged so that oxygen and fuel supplied for afterburning are mixed in advance.

Afterburning is performed when an aircraft takes off or when accelerating a sonic blast, but as mentioned above, when the locus temperature entering the turbine 60 is high, the combustion in the combustor 5 or the stoichiometric mixture ratio Since the combustion is carried out nearby, the amount of unburned oxygen contained in the combustion gas exiting the turbine 6 is small.
Therefore, when performing afterburning, the on-off valve 11 is turned on and the pump 10 is driven. Oxygen from the tank 12 is guided through the flow path 9 to the afterburner 7. In the afterburner 7, this oxygen burns the fuel, and this combustion leaves the turbine 6 and burns the combustion residue.
S1 was defeated on 11/11. This afterburning increases the temperature of the combustion gas.

It expands in the Noet nozzle 8, becomes a high-speed jet, and generates a strong propulsive force. When flying an aircraft at cruising speed, there is no need for afterburning, so pump 1
At the same time, the on-off valve 11 is closed to stop the supply of oxygen.

In this embodiment, the present invention is connected to a turbojet engine, but it goes without saying that the present invention can also be applied to a turbo fan engine or other gas turbine engine.

As explained above, in the present invention, 14. In order to increase the thermal efficiency of the gas turbine engine by 1j34, the turbine inlet was equipped with a means for introducing oxygen for the combustion of the tN charge in the gas turbine engine's 7-lid burner, and this oxygen was used for afterburning. Afterburning can be performed stably even when the temperature is high and the content of unburned oxygen in the combustion residue is low.

[Brief explanation of the drawing]

The drawing is a sectional view showing an embodiment of the present invention. 1...Gas turbine engine, 4...Compressor, 5...Combustor, 6...Turbine, 7...Afterburner, 8...Jet nozzle, 9...Flow path, 10...Pump, 11...
■Valve closed, 12...tank.

Claims (1)

[Claims] (1) A gas turbine engine equipped with a compressor, a combustor, a turbine, an afterburner, and a jet nozzle, characterized in that it is equipped with means for introducing oxygen for combustion of fuel in the afterburner. engine.