Variable area turbine
AssigneeUnited Technologies Corporation
InventorsFrederick M. Schwarz, Daniel Bernard Kupratis
Life of this patent
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Abstract
A gas turbine engine includes a shaft and a turbine configured to drive the shaft. The turbine has at least one stage comprising a plurality of turbine vanes interspersed with a plurality of turbine blades. The plurality of vanes includes at least one variable vane movable between a closed position to reduce air flow and an open position to increase air flow. Movement of the at least one variable vane is controlled based on an engine limiting condition.
Claims32
A gas turbine engine comprising:
- a shaft;
- a turbine configured to drive the shaft, the turbine including at least one stage comprising a plurality of turbine vanes adjacent a plurality of turbine blades;
- and
- wherein the plurality of vanes includes at least one variable vane movable between a closed position to reduce gaspath flow and an open position to increase gaspath flow, and wherein movement of the at least one variable vane is controlled based on at least one engine limiting condition wherein the at least one engine limiting condition comprises at least a takeoff condition, and wherein variable vane position is controlled based on inputs comprising at least fuel flow and ambient temperature to provide an output to control temperature at one or more desired engine locations.
A gas turbine engine comprising:
- a first shaft;
- a first turbine that drives the first shaft;
- a fan driven by the first shaft via a speed change mechanism;
- a second shaft rotatable relative to the first shaft;
- and
- a second turbine configured to drive the second shaft, the second turbine including at least one stage comprising a plurality of turbine vanes adjacent a plurality of turbine blades, and wherein the plurality of vanes includes at least one variable vane movable between an open position during a take-off condition and is selectively closed as the air craft progresses to a cruise condition, and wherein variable vane position is controlled based on inputs comprising at least fuel flow and ambient temperature to provide an output to control temperature at one or more desired engine locations.
A method for controlling a gas turbine engine comprising the steps of:
- (a) identifying at least one engine limiting condition that includes at least a takeoff condition;
- and
- (b) generating a control signal to actuate a control to move a variable turbine vane to a desired vane position to address the engine limiting condition;
- and
- (c) moving the variable vane via the control, where moving the variable vane is based on inputs comprising at least fuel flow and ambient temperature to provide an output to control temperature at one or more desired engine locations.
Dependencies are inferred from the claim text.