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US 4,062,183 AGranted
Fuel supply system for a gas turbine engine
AssigneeROLLS-ROYCE plc
InventorsDavid Omri Davies, Bruce Ernest Mills
Life of this patent
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Abstract
In order to improve the start-up of a gas turbine engine, a control system is provided which fills part of the fuel manifold with compressed air during start-up so as to prevent fuel flowing to all the burners and thereby to improve the performance of the remaining burners.
Claims9
A fuel supply system for a gas turbine engine having compressor means, combustion chamber and turbine means in flow series:
- a plurality of burners for injecting fuel into the combustion chamber;
- fuel manifold means operatively connected to each of said burners for sypplying fuel thereto;
- a source of compressed gas;
- a compressed gas operated starting device operatively connected to the compressor means and/or turbine means for starting the engine;
- duct means operatively connected to the source of compressed gas and to said compressed gas operated starting device and said fuel manifold means respectively, said duct means being arranged to supply compressed gas to said starting device for operating the same and to supply compressed gas to said fuel manifold means to act directly against fuel flowing therethrough to prevent fuel from being supplied to a predetermined number of burners;
- and
- valve means in said duct means upstream of the connection of the duct means to said starting device and upstream of the connection to said fuel manifold means for simultaneously supplying compressed gas to the starting device and the manifold means.
4 more elements
Dependencies are inferred from the claim text.