This engine is of great historical interest because it was the world’s first mass produced turbojet and one that saw extensive service in World War II. It was among the first engines to employ axial flow turbo machinery and straight through combustors.
Each of the six tubular combustors was supplied with fuel at pressures up to 5.2 MPa (750 psi) from a pressure-swirl atomizer, which sprayed the fuel upstream into the primary combustion zone. The primary air flowed into the liner through six swirl vanes, the amount of air being sufficient to achieve near-stoichiometric combustion at the engine design point.
Mixing between combustion products and dilution air was achieved using an assembly of stub pipes that were welded to a ring at their upstream end and to the outer perimeter of a 10-cm diameter dished baffle at their downstream end. The hot combustion products flowed radially outward through the gaps between the stub pipes to meet and mix with part of the cold secondary air.
The remaining secondary air flowed through the stub pipes, incidentally serving to protect them from burnout because of their immersion in the hot combustion gases, to provide further mixing of hot and cold gases in the recirculation zone created by the presence of the baffle.
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