A case for a gas turbine engine includes a core body. The core body defines a longitudinally extending core flow path, a laterally extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct.
A case for a gas turbine engine includes a core body. The core body defines a longitudinally extending core flow path, a laterally extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct. A heating element is connected to the core body and is in thermal communication with the structure-supporting member.
대표청구항▼
1. A case for a gas turbine engine, comprising: a core body, including: a longitudinally extending core flow path;a laterally extending bleed air duct coupling the core flow path in fluid communication with the external environment;a structure-supporting member spanning the bleed air duct; anda heat
1. A case for a gas turbine engine, comprising: a core body, including: a longitudinally extending core flow path;a laterally extending bleed air duct coupling the core flow path in fluid communication with the external environment;a structure-supporting member spanning the bleed air duct; anda heating element connected to the core body and in thermal communication with the structure-supporting member, configured to change an amount of heat output from the heating element if a programmed flight condition is met. 2. A case as recited in claim 1, wherein the structure-supporting member has a surface bounding the core flow path, wherein the heating element is coupled to the surface bounding the core flow path. 3. A case as recited in claim 1, wherein the core body defines a core body forward or aft segment coupled to the structure-supporting member, wherein the heating element is fixed to a surface of the forward or aft case segment bounding the bleed air duct. 4. A case as recited in claim 1, wherein the heating element is fixed to an exterior surface of the core body forward or aft of the structure-supporting member. 5. A case as recited in claim 1, wherein the structure-supporting member defines a structure-supporting member bore, wherein the heating element is seated in the bore. 6. A case as recited in claim 5, wherein the structure-supporting member bore extends axially relative to an axis of the core body. 7. A case as recited in claim 1, wherein the core body defines a bore forward or aft of the structure-supporting member, wherein the heating element is seated in the case bore. 8. A case as recited in claim 7, wherein the case bore extends radially relative to an engine rotation axis defined within the core body. 9. A case as recited in claim 1, wherein the heating element includes a resistive heating element. 10. A case as recited in claim 1, wherein the heating element includes a cartridge heater or a heater mat. 11. A case as recited in claim 1, wherein the structure-supporting member couples a core body forward segment to a core body forward or aft segment, wherein the structure-supporting member circumferentially divides the bleed air duct into first and second circumferentially adjacent bleed air ducts. 12. A case as recited in claim 11, wherein the structure-supporting member has a core flow path-facing surface for dividing airflow from the core flow path into a first bleed air duct flow and a second bleed air duct flow. 13. A system for heating a gas turbine engine case, comprising: a case core body, defining a longitudinally extending core flow path, a laterally extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct;a heating element connected to the core body and in thermal communication with the structure-supporting member;a controller operatively associated with the heating element;a memory communicative with the controller and having instructions recorded thereon that, where read by the processor, cause the processor to: determine a flight condition of an aircraft;compare the flight condition to a programmed condition to determine whether the preprogrammed flight condition is met; andchange an amount electrical power applied to the heating element if comparing the flight condition to the programmed condition operation determines that the programmed flight condition is met. 14. A system as recited in claim 13, wherein the flight condition is operation in a portion of flight envelop where hail or ice ingestion is expected. 15. A system as recited in claim 13, wherein the flight condition is descent. 16. A system as recited in claim 13, where the flight condition is descent and hail or ice ingestion is expected. 17. A system recited in claim 13, wherein the change in the amount of electrical power includes (a) an increase in electrical power when the programmed flight condition is met, and (b) a decrease in electrical power when the programmed flight condition is not met. 18. A method of protecting a gas turbine engine, the method comprising: determining a flight condition of an aircraft;comparing the flight condition to a programmed condition;changing an amount electrical power applied to a heating element when comparing the flight condition to the programmed condition operation determines that the programmed flight condition is met; andwherein the heating element is in thermal communication with a structure-supporting member spanning a bleed air duct defined between forward and aft segments of gas turbine engine core body. 19. A method as recited in claim 18, wherein the flight condition is a flight condition where hail or ice ingestion is expected. 20. A method as recited in claim 18, wherein changing the amount of electrical power includes (a) increasing the electrical power applied to the heating element when the programmed flight condition is met, and (b) decreasing the electrical power applied to the heating element when the programmed flight condition is not met.
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이 특허에 인용된 특허 (1)
Frost Wilson (Fairfield OH) Wood Peter J. (Cincinnati OH) Bobo Melvin (Cincinnati OH) Little Daniel R. (West Chester OH), Method and apparatus for ejecting foreign matter from the primary flow path of a gas turbine engine.
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