Abstract: A flameholder of a burner for a gas turbine engine includes a discrete pattern of judiciously shaped apertures having projectiles in the form of cusps formed on the upstream face facing the airstream so as to improve the flameholder with a consequential reduction in the concentration level of gaseous pollutants.

Abstract: A method for producing a permanent combustion under detonating or substanlly detonating conditions within a stream flowing at supersonic speed, consisting in subdividing a stream of combustion-sustaining fluid into two parallel streams, modifying the speed of at least one of said streams, causing said streams flowing at different speeds to meet again inside an area wherein a diabolo-shaped system of shock waves is formed and injecting fuel into the stream flowing at the higher speed, the combustion starting on the downstream side of a flat surface extending perpendicularly to the direction of flow and forming the surface of minimum cross-sectional area of the diabolo-shaped system.

Abstract: The disclosure of this invention pertains to an annular combustion chamber for a gas turbine engine. The chamber has at its upstream end an annular array of baffles defining inlet passages for air or air/fuel mixture. The baffles overlap in the circumferential sense so that air or air/fuel mixture entering passages is directed by the baffles into a circumferential swirl. Those surfaces of the baffles which are open to the interior of the chamber are swept by the fluid emerging from the passages to be cooled thereby.

Abstract: A partial swirl augmentor for a turbofan engine having an annular duct for directing hot gases into the augmentor combustion chamber. Located within the combustion chamber is a piloted vee-gutter flameholder system which has a circumferential pilot located at the outer edge of the swirlng hot turbine exhaust gas stream. As a result thereof, the partial swirl augmentor can attain state-of-the art engine after burning thrust levels with an increased altitude blow-out limit.

Abstract: A combustion chamber for gas turbines with a variable inlet cross section for the primary air, whereby the inlet cross section is so varied in dependence on the fuel pressure determining the injection quantity that with an increasing or decreasing fuel pressure, the inlet cross section is increased or decreased.

Abstract: A combustion chamber having an end-wall at the inlet side and an axial inlet opening, which is adjoined by an essentially cylindrical wall section provided with secondary air inlet openings; the end-wall thereby adjoins the inlet opening approximately hemispherically shaped with a sphere diameter which is larger than the diameter of the cylindrical wall section while the adjoining combustion chamber portion is again reduced to the adjacent cylindrical wall section by way of a combustion chamber wall substantially continuing the sphere shape; the fuel injection device is provided upstream of the inlet opening which injects fuel into the inlet opening, itself covered off by a deflection means.