Rolls-royce Corporation

William C Kwan

Anthony Pidcock

Desmond Close

A combustion chamber for a gas turbine engine has a wall which is provided with rows of apertures. The apertures are arranged so that the axes of the apertures form an angle of between 25.degree. and 35.degree. with respect to the inner surface of the wall. The apertures have a first cylindircal portion and a second divergent portion to produce fan shaped apertures. An upstream portion of the wall has apertures arranged in axially spaced groups, each of which has three rows of apertures and a downstream portion of the wall has apertures arranged in axially spaced groups, each of which has two rows of apertures. The axes of adjacent apertures in each row are spaced apart by at least three times the diameter of the cylindrical portion. The apertures produce effective film cooling of the wall using less cooling air than conventional cooling rings. The apertures may be arranged locally to cope with hot spots.

Combustion chamber for a gas turbine engine

A gas turbine engine combustion apparatus for vaporizing fuel comprises a flame tube having an upstream end wall in which are located a number of flow guides having associated fuel ducts. In operation, fuel and air flow through the U-shaped duct in each guide and the fuel flows onto the inside of the end wall which acts as a vaporizing surface. The exterior of the end wall is cooled by a flow of air from the engine compressor. The invention avoids the need of vaporizing tubes within the flame tube.

Gas turbine engine combustion apparatus

A gas turbine engine fuel burner comprises a convergent/divergent flow passage which receives a flow of swirling fuel and air upstream of the passage throat. The fuel and air mixture passes through the throat and is entrained into a further mass of swirling air which enters the passage through air swirlers in the wall of the divergent portion of the passage. The invention is intended to promote good fuel and air mixing, fine atomization and a reduction in carbon deposition on the burner.

Fuel burners

This invention relates to a method of manufacturing laminated material. Particularly to laminated materials for use in the construction of flame tubes of gas turbine engines. The laminated material is manufactured from three sheets, a central sheet, a first sheet, and a second sheet. The central sheet is perforated with an arrangement of equi-spaced apertures. The central sheet with apertures is then secured to the first sheet. A number of channels are machined through the central sheet to leave the first sheet and an arrangement of equi-spaced lands secured thereto. The first sheet is perforated with an arrangement of equi-spaced apertures to form air entry holes. The second sheet is then secured to the assembly to form a laminated material comprising a first sheet with apertures and second sheet separated by an arrangement of equi-spaced lands machined from central sheet.

Manufacture of laminated material

The airflow into a gas turbine engine combustion chamber e.g. through the primary air inlet and the dilution air inlets is directionally controlled by airflow directing inserts located in the air inlets. The inserts preferably comprise an open-ended cellular honeycomb structure.

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Derby, United Kingdom

William C Kwan