Gas turbine engine having a turbomachine and an electric motor coupled to a propeller
A gas turbine engine including: a turbomachine coupled to a propeller of the gas turbine engine, the turbomachine being in fluid communication with an external environment through an air inlet; and an electric motor coupled to the propeller, wherein the air inlet is in fluid communication with a bypass duct having a selectively variable geometry.
1. A gas turbine engine comprising:
a propeller;
a turbomachine coupled to the propeller, the turbomachine being in fluid communication with an external environment through an air inlet; and
an electric motor coupled to the propeller,
wherein the air inlet is in fluid communication with a bypass duct having a selectively variable geometry downstream of the propeller,
wherein the bypass duct comprises an adjustable flap configured to selectively adjust a fluid flow rate of air passing through the bypass duct, in which the adjustable flap increases an opening size of the bypass duct automatically in response to switching operation from the turbomachine to the electric motor.
2. The gas turbine engine of claim 1 ,
wherein the bypass duct defines a first fluid volumetric flow rate capability when the electric motor is active and a second fluid volumetric flow rate capability when the electric motor is inactive, and wherein the first fluid volumetric flow rate capability is higher than the second fluid volumetric flow rate capability.
3. The gas turbine engine of claim 1 , wherein at least one of the air inlet and bypass duct is configured to mitigate back pressure of the propeller when the propeller is driven at least in part by the electric motor.
4. The gas turbine engine of claim 1 , wherein the adjustable flap is configured to be rotated between a plurality of positions.
5. The gas turbine engine of claim 1 , wherein the adjustable flap is configured to be translated between a plurality of positions.
6. A hybrid electric gas turbine engine comprising:
a propeller;
an electric motor configured to selectively drive the propeller of the gas turbine engine when a secondary drive element of the hybrid electric gas turbine engine is operating at a reduced capacity; and
a bypass duct comprising an adjustable flap downstream of the propeller configured to increase a fluid volumetric flow rate capability of the bypass duct when the electric motor is active,
wherein the secondary drive element comprises a turbomachine, and
wherein the adjustable flap is configured to increase an opening size of the bypass duct automatically in response to switching operation from the turbomachine to the electric motor.
7. The hybrid electric gas turbine engine of claim 6 , wherein the turbomachine is in fluid communication with an external environment through an air inlet, and wherein the turbomachine is in fluid communication with the air inlet upstream of the bypass duct.
8. The hybrid electric gas turbine engine of claim 6 , wherein the adjustable flap is configured to automatically adjust between two or more positions in response to activation of the electric motor.
9. The hybrid electric gas turbine engine of claim 6 , wherein the adjustable flap is configured to mitigate back pressure of the propeller driven at least in part by the electric motor.
10. The hybrid electric gas turbine engine of claim 6 , wherein the adjustable flap is configured to rotate, translate, or both.
11. A method of using a gas turbine engine, the method comprising:
driving a propeller of the gas turbine engine using a turbomachine;
switching from the turbomachine to an electric motor for driving the propeller; and
increasing an opening size of a bypass duct of the gas turbine engine downstream of the propeller to increase volumetric flow rate of air through the bypass duct when the electric motor is active,
wherein increasing the opening size is performed automatically in response to switching from the turbomachine to the electric motor.
12. The method of claim 11 , wherein increasing the opening size is performed by rotating a rotatable flap in fluid communication with the bypass duct so as to increase an area of the bypass duct.
13. The method of claim 11 , wherein increasing the opening size is performed by translating a translatable flap in fluid communication with the bypass duct so as to increase an area of the bypass duct.
14. The method of claim 11 , wherein increasing the opening size increases a fluid volumetric flow rate capability of the bypass duct.
15. The method of claim 11 , wherein increasing the opening size of a bypass duct reduces back pressure within the gas turbine engine upstream of the turbomachine.
16. The method of claim 11 , further comprising:
switching from the electric motor back to the turbomachine for driving the propeller; and
decreasing the opening size of a bypass duct of the gas turbine engine to decrease volumetric flow rate of air through the bypass duct when the electric motor is inactive.
17. The method of claim 11 ,
wherein the gas turbine engine comprises an air inlet in fluid communication with the turbomachine and the bypass duct, and
wherein a volumetric flow rate of air entering the air inlet is approximately equal when the propeller is driven by the turbomachine and when the propeller is driven by the electric motor.
18. The method of claim 11 , wherein an aerodynamic resistance of the gas turbine engine is not affected by switching from the turbomachine to the electric motor.