Bowed rotor nacelle cooling

Patent metadata

Field	Value
Publication number	US-10427632-B2
Application number	US-201715475987-A
Country	US
Kind code	B2
Filing date	Mar 31, 2017
Priority date	Mar 31, 2017
Publication date	Oct 1, 2019
Grant date	Oct 1, 2019

Abstract

The present disclosure describes ventilation systems having a reduced aerodynamic footprint. The vents in the ventilation systems are actuated with Shape Memory Alloys that actuate the vents on an as needed basis while effectively sealing the vents when not in operation. The present disclosure further describes a ventilation system in an aircraft nacelle that helps mitigate bowed rotors by cooling down the engine nacelle faster or by helping create a uniform temperature distribution in the nacelle. In various embodiments, the ventilation system comprises vents and fans embedded in the vents.

First claim

What is claimed is:

1. An apparatus, comprising:
a housing;
a vent disposed in the housing; and
a shape-memory alloy (SMA) element coupled to the vent and configured such that when a temperature in the housing exceeds a threshold, the SMA element changes shape to actuate the vent;
wherein air flows through the vent to cool an inside of the housing when the vent is actuated; and
wherein:
the housing is an engine pylon, an electronics and equipment bay on an aircraft, or a battery container, or
the apparatus is a nacelle in combination with a gas turbine and the housing is the nacelle, or
the housing includes a grille covering a portion of an automobile engine.

2. The apparatus of claim 1 , wherein the housing is the engine pylon, the electronics and equipment bay, or the battery container.

3. The apparatus of claim 1 , wherein:
the apparatus is the nacelle in combination with the gas turbine engine, and
the housing is the nacelle.

4. The apparatus of claim 1 , wherein the vent is modular.

5. The apparatus of claim 1 , wherein the housing is the grille covering a portion of the automobile engine.

6. In combination, an engine housing and a gas turbine engine comprising a rotor shaft, the engine housing comprising:
a wall; and
a plurality of vents disposed in the wall so that airflow through the vents reduces or prevents thermal bowing of the rotor shaft caused by a temperature gradient across the rotor shaft.

7. The combination of claim 6 , further comprising a fan attached to the wall and coupled to at least one of the vents.

8. The combination of claim 7 , wherein the fan is disposed inside the at least one of the vents.

9. The combination of claim 6 , further comprising a plurality of fans attached to the wall and coupled to the vents, wherein:
at least one of the fans is disposed to direct flow of air from inside the engine housing to an outside of the engine housing through at least one of the vents in an upper region of the engine housing, and
at least one of the fans is disposed to direct flow of air from the outside the engine housing to the inside the engine housing through at least one of the vents in a lower region of the engine housing.

10. The combination of claim 6 , further comprising a plurality of fans attached to the wall and coupled to the vents, wherein:
at least one of the fans is disposed to direct air from an inside the engine housing to an outside of the engine housing through at least one of the vents in a lower region of the engine housing, and
at least one of the fans is disposed to direct air from the outside of the engine housing to the inside the engine housing through at least one of the vents in an upper region of the engine housing.

11. The combination of claim 6 , further comprising a plurality of fans attached to the wall and coupled to the vents, wherein the fans are disposed to direct air from an outside of the engine housing to an inside the engine housing and push hotter air out a rear of the gas turbine engine.

12. The combination of claim 6 , further comprising a plurality of fans attached to the wall and coupled to the vents, wherein the fans are disposed to swirl air around the engine housing and push hotter air out a rear of the engine.

13. The combination of claim 6 , further comprising at least one of the vents in an upper half of the engine housing and at least one of the vents in a lower half of the engine housing.

14. The combination of claim 6 , further comprising barriers pivotally attached to the wall so as to swing open or closed under gravity, thereby sealing or unsealing the vents.

15. The combination of claim 6 , further comprising barriers pivotally attached to the wall so as to swing closed and seal each the vents upon pressure from airflow outside the engine housing when the airflow is moving above a threshold velocity.

16. The combination of claim 6 , further comprising barriers pivotally attached to the wall so as to swing open or closed, thereby sealing and unsealing the vents, wherein the barrier comprises a shape-memory alloy (SMA) element.

17. A method of cooling a rotor shaft in an aircraft engine assembly, comprising:
re-distributing flow of air trapped in an engine housing, when the rotor shaft in the engine housing is cooling down in a temperature gradient perpendicular to a longitudinal axis of the rotor shaft, thereby reducing or preventing thermal bowing of the rotor shaft in the temperature gradient.

18. The method of claim 17 , further comprising providing one or more ventilation ducts in the engine housing, wherein the re-distributing comprises:
allowing flow of air into a bottom of the engine housing through at least one of the ventilation ducts and expelling hotter air out of a top of the engine housing through at least one of the ventilation ducts; and/or
allowing flow of air into a top of the engine housing through at least one of the ventilation ducts and expelling hotter air out of a bottom of the engine housing through at least one of the ventilation ducts; and/or
using the ventilation ducts to swirl cooler air around the engine housing and push hotter air out a rear of an aircraft engine assembly; and/or
allowing flow cooler air into the engine housing through the ventilation ducts so as to push hotter air out a rear of the aircraft engine assembly.

19. The method of claim 17 , further comprising using fans attached to the engine housing to create convection of the air that subjects the rotor shaft to a more uniform temperature.

20. The method of claim 17 , further comprising providing one or more ventilation ducts in the engine housing and one or more fans attached to the engine housing, wherein the re-distributing comprises using the fans to push or suck air through the ventilation ducts.

Assignees

• Boeing Co

Inventors

• Jackowski Jason J
• Karnofski Kent E
• Calkins Frederick T

Classifications

• F01D25/26

  Double casings; Measures against temperature strain in casings · CPC title

• B64D2033/024

  comprising cooling means · CPC title

• F01D25/14

  Casings modified therefor (double casings F01D25/26) · CPC title

• B64D33/08

  of power plant cooling systems · CPC title

• B60R19/52 Primary

  Radiator or grille guards {; Radiator grilles (cooling aspects B60K11/08)} · CPC title