Thermally actuated passive gas turbine engine compartment venting

• US 8,991,191 B2
• Filed: 11/24/2009
• Issued: 03/31/2015
• Est. Priority Date: 11/24/2009
• Status: Active Grant

• Current Assignee: General Electronics Company
• Original Assignee: General Electric Company
• Inventors: Diaz, Carlos Enrique, Laborie, Daniel Jean-Louis, Geary, Stephen Dennis
• Primary Examiner(s): Gartenberg, Ehud
• Assistant Examiner(s): Subramanian, Karthik
• Application Number:
  US12/624,858
• Publication Number:
  US 20110120075A1
• Time in Patent Office: 1,953 Days
• Field of Search: 607/82, 607/85, 607/95, 60/390.91, 602/261, 602/262, 602/263, 602/29, 602/30, 417/208, 417/321, 251/11
• US Class Current: 60/795
• CPC Class Codes: B64D 2033/024 comprising cooling means
• CPC Class Codes: B64D 2045/009 Fire detection or protection; Erosion protection, e.g. from airborne particles
• CPC Class Codes: B64D 29/00 Power-plant nacelles, fairings, or cowlings nacelles not otherwise provided for B64C
• CPC Class Codes: F01D 25/14 Casings modified therefor double casings F01D25/26
• CPC Class Codes: F02K 1/383 with retractable elements
• CPC Class Codes: F02K 1/822 Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
• CPC Class Codes: F05D 2260/20 Heat transfer, e.g. cooling
• CPC Class Codes: F05D 2270/09 to cope with emergencies
• CPC Class Codes: F05D 2270/112 by limiting temperatures
• CPC Class Codes: F05D 2270/3032 excessive temperatures, e.g. caused by overheating
• CPC Class Codes: F05D 2270/64 Hydraulic actuators
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A thermally actuated venting system includes a thermally actuated vent for opening a vent outlet in a gas turbine engine associated compartment with a passive thermal actuator located in the compartment based on a temperature of the compartment. Outlet may be located at or near a top of a core engine compartment, a fan compartment, or a pylon compartment. Actuator may be operably connected to a hinged door of vent for opening outlet. Actuator may be actuated by a phase change material disposed in a chamber and having a liquid state below a predetermined actuation temperature and a gaseous state above the predetermined actuation temperature. Actuator may include a thermal fuse for closing door during a fire. Thermal fuse may include at least a portion of piston rod or a cylinder wall of actuator being made of a fuse material having a melting point substantially above the predetermined actuation temperature.

Claims

1. A thermally actuated venting system comprising:

a thermally actuated air vent for opening an air vent outlet in a gas turbine engine associated compartment, the vent outlet located at or near the top of the compartment,

a passive thermal actuator in the compartment, the thermally actuated air vent including a hinged door operably connected to the passive thermal actuator for opening the vent outlet, a thermal fuse incorporated in the thermal actuator for closing the door during a fire in the compartment,

the thermal actuator operable for opening the thermally actuated air vent based on a temperature of the compartment and venting hot air from the compartment, the thermal actuator including a piston disposed within a cylinder, a chamber within the cylinder between the piston and a bottom wall of the cylinder, a piston rod extending upwardly from the piston through an aperture in a top wall of the cylinder, a distal end of the piston rod connected to the hinged door, and

a phase change material in the chamber having a liquid state below a predetermined actuation temperature and a gaseous state above the predetermined actuation temperature,

the thermal fuse including the piston rod or a portion of the piston rod made of a fuse material having a melting point above the predetermined actuation temperature and the melting point being in a range between 786 and 1202 degrees Fahrenheit.

2. The system of claim 1, further comprising the associated compartment being a fan compartment between a gas turbine engine fan cowl and a gas turbine engine fan casing and an electronic engine control mounted in the fan compartment.

3. The system of claim 1, further comprising the associated compartment being a core engine compartment circumscribed by a core engine cowl.

4. The system of claim 1, further comprising the associated compartment being a pylon compartment in a pylon for mounting an engine above an aircraft wing.

5. The system of claim 4, further comprising:

the thermal actuator including a piston disposed within a cylinder,

the pylon compartment located inside of the pylon and surrounded at least in part by a pylon fairing,

the thermally actuated vent disposed in a top wall upwardly bounding the pylon compartment, and

the top wall being part of an engine exhaust deflector.

6. A thermally actuated venting system comprising:

a thermally actuated air vent for opening an air vent outlet in a gas turbine engine associated compartment, the vent outlet located at or near the top of the compartment,

a passive thermal actuator in the compartment, the thermally actuated air vent including a hinged door operably connected to the passive thermal actuator for opening the vent outlet, a thermal fuse incorporated in the thermal actuator for closing the door during a fire in the compartment,

the thermal actuator operable for opening the thermally actuated air vent based on a temperature of the compartment and venting hot air from the compartment, the thermal actuator including a piston disposed within a cylinder, a chamber within the cylinder between the piston and a bottom wall of the cylinder, a piston rod extending upwardly from the piston through an aperture in a top wall of the cylinder, a distal end of the piston rod connected to the hinged door, and

a phase change material in the chamber having a liquid state below a predetermined actuation temperature and a gaseous state above the predetermined actuation temperature,

the thermal fuse including an annular cylinder wall of the cylinder or a portion of the cylinder wall made of a fuse material having a melting point above the predetermined actuation temperature and the melting point being in a range between 786 and 1202 degrees Fahrenheit.

7. The system of claim 6, further comprising the associated compartment being a fan compartment between a gas turbine engine fan cowl and a gas turbine engine fan casing and an electronic engine control mounted in the fan compartment.

8. The system of claim 6, further comprising the associated compartment being a core engine compartment circumscribed by a core engine cowl.

9. The system of claim 6, further comprising the associated compartment being a pylon compartment in a pylon for mounting an engine above an aircraft wing.

10. The system of claim 9, further comprising:

the thermal actuator including a piston disposed within a cylinder,

the pylon compartment located inside of the pylon and surrounded at least in part by a pylon fairing,

the thermally actuated vent disposed in a top wall upwardly bounding the pylon compartment, and

the top wall being part of an engine exhaust deflector.