Dual function air diverter and variable area fan nozzle
AssigneeUnited Technologies Corporation
InventorRichard Alan Weiner
Life of this patent
Estimating the term…
Abstract
A modulating fan air diverter and annular air-oil cooler for a gas turbine engine located in the inner fixed structure adjacent to the core cowl is provided. The fan air diverter modulates between an open position, corresponding to maximum fan nozzle area and airflow through the air-oil cooler, and a closed position, corresponding to minimum fan nozzle area and airflow through the air-oil cooler. As such, the device is capable of supporting dual functions of engine heat management as well as engine performance and fan stability.
Claims20
A fan air diverter for a gas turbine engine having at least an inner cowl and an annular air-oil cooler, the fan air diverter comprising:
- a nozzle flap disposed about the inner cowl and coaxially adjacent to the annular air-oil cooler, the nozzle flap being pivotally coupled to the inner cowl and selectively movable relative to the annular air-oil cooler between an open position and a closed position;
- and
- an actuation system assembly operatively coupling the nozzle flap to the inner cowl, the actuation system assembly being configured to actuate the nozzle flap between the open position and the closed position, wherein the actuator system comprises:
- at least one sync ring operatively coupled to the nozzle flap, the sync ring being rotatable between a first angular position and a second angular position about an axis of the gas turbine engine, wherein rotation of the sync ring to the first angular position moves the nozzle flap to the open position, and rotation of the sync ring to the second angular position moves the nozzle flap to the closed position.
An oil cooling assembly for a gas turbine engine having at least an inner cowl, comprising:
- an annular air-oil cooler disposed about the inner cowl, the annular air-oil cooler including an integral annular oil tank and a plurality of cooling fins radially extending therefrom, the cooling fins being disposed in at least partial communication with a fan duct and a fan nozzle;
- and
- a fan air diverter disposed about the inner cowl and coaxially adjacent to the cooling fins, the fan air diverter being selectively movable relative to the cooling fins to provide at least one of a converging fan airflow through the fan nozzle and the cooling fins, a converging-diverging fan airflow through the fan nozzle and the cooling fins, and a fan airflow that converges toward an outlet-side of the cooling fins.
A gas turbine engine, comprising:
- an outer nacelle;
- an inner cowl defining a fan duct and nozzle along with the outer nacelle for receiving fan airflow;
- an annular air-oil cooler disposed circumferentially about the inner cowl and in communication with the fan nozzle;
- at least one nozzle flap disposed about the inner cowl and coaxially adjacent to the annular air-oil cooler, the nozzle flap being pivotally coupled to the inner cowl and selectively movable relative to the annular air-oil cooler between an open position and a closed position;
- and
- an actuation system assembly operatively coupling the nozzle flap to the inner cowl, the actuation system assembly being configured to actuate the nozzle flap between the open position and the closed position so as to modulate fan airflow and to provide at least one of a converging fan airflow through the fan nozzle and the cooling fins, a converging-diverging fan airflow through the fan nozzle and the cooling fins, and a fan airflow that converges toward an outlet-side of the cooling fins.
Dependencies are inferred from the claim text.