Integrated actuator module for gas turbine engine
An actuator module for a gas turbine engine includes a multiple of actuators mounted within a common actuator housing.
1. An actuator module for a gas turbine engine comprising:
an actuator housing;
a first actuator mounted within said actuator housing, said first actuator operable to actuate a first variable vane set; and
a second actuator mounted within said actuator housing, said second actuator operable to actuate a second variable vane set.
2. The actuator module as recited in claim 1 , further comprising a third actuator mounted within said actuator housing, said third actuator operable to actuate a bleed valve system.
3. The actuator module as recited in claim 2 , wherein said bleed valve system comprises a 2.5 bleed valve actuator system.
4. The actuator module as recited in claim 1 , wherein said actuator housing is mountable to an accessory gearbox.
5. The actuator module as recited in claim 1 , wherein said actuator housing is mountable to an engine static structure.
6. The actuator module as recited in claim 1 , wherein said actuator housing is mountable to an intermediate case (IMC).
7. The actuator module as recited in claim 1 , wherein said first variable vane set is a low pressure compressor variable vane set.
8. The actuator module as recited in claim 1 , wherein said second variable vane set is a high pressure compressor variable vane set.
9. A gas turbine engine comprising:
a static structure;
a core engine;
a gear system supported by said static structure;
a fan section driven by said core engine through said gear system;
an actuator housing mounted to said static structure;
a first actuator mounted within said actuator housing, said first actuator operable to actuate a first variable vane set of said core engine; and
a second actuator mounted within said actuator housing, said second actuator operable to actuate at least one second variable vane set.
10. The engine as recited in claim 9 , wherein said first variable vane set is a low pressure compressor variable vane set.
11. The engine as recited in claim 9 , wherein said second variable vane set is a high pressure compressor variable vane set.
12. The engine as recited in claim 9 , wherein said gear system defines a gear reduction ratio of greater than or equal to about 2.3.
13. The engine as recited in claim 9 , wherein said gear system defines a gear reduction ratio of greater than or equal to about 2.5.
14. The engine as recited in claim 9 , wherein said gear system defines a gear reduction ratio of greater than or equal to 2.5.
15. The engine as recited in claim 9 , wherein said core engine includes a low pressure turbine which defines a pressure ratio that is greater than about five (5).
16. The engine as recited in claim 9 , wherein said core engine includes a low pressure turbine which defines a pressure ratio that is greater than five (5).
17. The engine as recited in claim 9 , wherein said fan section is mounted within a fan nacelle and said core engine is mounted within a core nacelle, said fan nacelle mounted at least partially around said core nacelle to define a fan bypass flow path for a fan bypass airflow, said fan bypass airflow defines a bypass ratio greater than about six (6).
18. The engine as recited in claim 17 , wherein said bypass airflow defines a bypass ratio greater than about ten (10).
19. The engine as recited in claim 18 , wherein said bypass flow defines a bypass ratio greater than ten (10).