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AssigneeROLLS-ROYCE plc
InventorAnthony B Parry
Estimating the term…
Within an intake for a gas turbine engine provision is provided through stator vanes 25, 45 in the stator whereby back pressure from a necessary obstruction 34, 46 can be utilised to balance forward pressure variations caused by intake droop or crosswinds in order to reduce those forward pressure detriments for more efficient engine operation according to a desired objective regime. Typically the flow through the intake 20 is analysed and then an appropriate positioning of the stator vanes 25, 45 determined in order to provide approximate balance between the forward pressures and back pressures. Normally, a combination of camber variation of stator vanes 45a and stagger variation of stator vanes 45b are utilised in order to achieve a desired momentum balance around the circumference of the intake 20. It will be understood that both the forward pressures and the back pressures are differentially variable about the circumference such that one opposes the other.
A gas turbine engine comprising an intake, a low pressure compressor including a plurality of rotor blades arranged downstream of the intake, a plurality of stator vanes arranged downstream of the low pressure compressor and at least one obstruction arranged downstream of the stator vanes, whereby in use the at least one obstruction produces a circumferentially varying back pressure on the stator vanes and the intake supplies an airflow having a circumferentially varying forward flow pressure to the low pressure compressor due to a non-axisymmetric flow of air into the intake, the stator vanes being arranged to balance the circumferentially varying back pressure from the at least one obstruction with the circumferentially varying forward flow pressure from the intake at substantially all circumferential positions, said stator vanes having variable camber and stagger configurations at different circumferential positions so as to balance the varying back pressure caused by the said at least one obstruction.
A gas turbine engine comprising an intake, a low pressure compressor including a plurality of rotor blades arranged downstream of the intake, a plurality of stator vanes arranged downstream of the low pressure compressor and at least one obstruction arranged downstream of the stator vanes, whereby in use the at least one obstruction produces a circumferentially varying back pressure on the stator vanes and the intake supplies an airflow having a circumferentially varying forward flow pressure to the low pressure compressor due to a non-axisymmetric flow of air into the intake, the stator vanes being arranged to balance the circumferentially varying back pressure from the at least one obstruction with the circumferentially varying forward flow pressure from the intake at substantially all circumferential positions, wherein the stator vanes at different circumferential positions have different stagger angles.
A gas turbine engine comprising an intake, a low pressure compressor including a plurality of rotor blades arranged downstream of the intake, a plurality of stator vanes arranged downstream of the low pressure compressor and at least one obstruction arranged downstream of the stator vanes, whereby in use the at least one obstruction produces a circumferentially varying back pressure on the stator vanes and the intake supplies an airflow having a circumferentially varying forward flow pressure to the low pressure compressor due to a non-axisymmetric flow of air into the intake, the stator vanes being arranged to balance the circumferentially varying back pressure from the at least one obstruction with the circumferentially varying forward flow pressure from the intake at substantially all circumferential positions, wherein the stator vanes have different camber configurations at different circumferential positions.
A method of analyzing a gas turbine engine comprising an intake, a low pressure compressor including a plurality of rotor blades arranged downstream of the low pressure compressor and at least one obstruction arranged downstream of the stator vanes, in use that at least one obstruction producing a circumferentially varying back pressure on the stator vanes and the intake supplying an airflow having a circumferentially varying forward pressure to the low pressure compressor, the method comprising the steps of:
A method analyzing a gas turbine engine comprising an intake, a low pressure compressor including a plurality of rotor blades arranged downstream of the intake, a plurality of stator vanes arranged downstream of the low pressure compressor and at least one obstruction arranged downstream of the stator vanes, in use the at least one obstruction producing a circumferentially varying back pressure on the stator vanes and the intake supplying an airflow having a circumferentially varying forward pressure to the low pressure compressor, the method comprising the steps of;
Dependencies are inferred from the claim text.