Turbofan bypass air cooled oil cooler fairings

Patent metadata

Field	Value
Publication number	US-9982630-B2
Application number	US-201514721412-A
Country	US
Kind code	B2
Filing date	May 26, 2015
Priority date	May 26, 2015
Publication date	May 29, 2018
Grant date	May 29, 2018

Abstract

A cooler assembly disposed in and cooled by an air stream according to one embodiment includes a cooler matrix and a fairing. The fairing assembly is disposed generally around the cooler matrix and includes side fairing-housings, first and second side fairing-housings being joined to one another at respective leading and trailing edges, the leading edges partially defining a cooler inlet and the trailing edges partially defining a cooler outlet, the first and second side fairing-housing trailing edges angled transversely toward each other to define a trapezoidal shape for the outlet.

First claim

The invention claimed is:

1. A cooler assembly for a gas turbine engine, the cooler assembly disposed in a duct of the gas turbine engine for cooling by an air stream through the duct, the cooler assembly comprising:
a cooler matrix in fluid communication with an engine fluid system to be cooled and a fairing assembly disposed to at least partially house the cooler matrix, the fairing assembly having a first side fairing-housing and a second side fairing-housing, each of the first side fairing-housing and the second side fairing-housing having a respective leading edge and a respective trailing edge, the respective leading edges being indirectly connected within the fairing assembly and the respective trailing edges being indirectly connected within the fairing assembly, the respective leading edges partially defining a cooler inlet and the respective trailing edges partially defining a cooler outlet, the cooler outlet including an inner side and an outer side respectively interconnecting the respective trailing edges of the first side fairing-housing and the second side fairing-housing, the respective trailing edges of the first side fairing-housing and the second side fairing-housing being angled transversely toward each other such that the inner side of the cooler outlet is shorter than the outer side of the cooler outlet.

2. The cooler assembly as defined in claim 1 , wherein the inner side of the cooler outlet is disposed in the air stream within the duct and the outer side of the cooler outlet is adjacent a wall of the duct.

3. The cooler assembly as defined in claim 2 , wherein a rear fairing provides the indirect connection between the respective trailing edges of the first side fairing-housing and the second side fairing-housing in the fairing assembly, and wherein the rear fairing comprises a concave profile.

4. The cooler assembly as defined in claim 1 , wherein the first side fairing-housing has a maximum transverse dimension greater than a maximum transverse dimension of the second side fairing-housing, the first side fairing-housing accommodating a valve attached to a sides of the cooler matrix.

5. The cooler assembly as defined in claim 1 , wherein the cooler inlet has a trapezoidal shape.

6. A gas turbine engine having a duct with an air stream passing therethrough, the gas turbine engine comprising:
a cooler assembly disposed in the duct and attached to a duct wall, the cooler assembly including a cooler matrix in fluid communication with fluid system of the gas turbine engine, first and second side fairing-housings circumferentially spaced apart from each other, first and second front fairings radially spaced apart from each other and extending in a downstream direction toward the cooler matrix and extending transversely between respective front portions of the first and second side fairing-housings to form an inlet for directing a portion of the air stream to enter and pass through the cooler matrix, a first rear fairing positioned downstream of the cooler matrix and extending transversely between respective rear portions of the first and second side fairing-housings, the respective rear portions of the first and second side fairing-housings and an inner surface of the first rear fairing directing the portion of the air stream which has passed through and which has been discharged from the cooler matrix,
wherein respective trailing edges of each of the first side fairing-housing and the second side fairing-housing each define an obtuse angle with respect to the inner surface of the first rear fearing.

7. The gas turbine engine as defined in claim 6 , wherein the cooler assembly further comprises a second rear fairing having an inner surface spaced apart from and facing toward the inner surface of the first rear fairing, the second rear fairing extending transversely between the respective rear portions of the first and second side fairing-housings, the respective trailing edges of each of the first side fairing-housing and the second side fairing-housing each defining an acute angle with respect to the inner surface of the second rear fairing.

8. The gas turbine engine as defined in claim 6 , wherein the cooler assembly further comprises a second rear fairing extending transversely between the respective rear portions of the first and second side fairing-housings, the respective rear portions of the first and second side fairing-housings, in combination, defining an outlet for directing the portion of the air stream which has passed through and which has been discharged from the cooler matrix.

9. The gas turbine engine as defined in claim 6 , wherein respective trailing edges of the first side fairing-housing and the second side fairing-housings and respective downstream edges of the first rear fairing and the second rear fairing, in combination, define an outlet, the downstream edge of the first rear fairing being shorter than the downstream edge of the second rear fairing.

10. The gas turbine engine as defined in claim 6 , wherein the first rear fairing extends in the downstream direction and terminates to form a downstream edge thereof, the downstream edge of the first rear fairing being positioned upstream of the trailing edges of the first and second side fairing-housings.

11. The gas turbine engine as defined in claim 6 , wherein the first rear fairing extends in the downstream direction and terminates to form a downstream edge thereof, the downstream edge of the first rear fairing defining a concave profile.

12. The gas turbine engine as defined in claim 6 , wherein the first side fairing-housing has a maximum transverse dimension greater than a maximum transverse dimension of the second side fairing-housing, the first side fairing-housing accommodating a header side of the cooler matrix and a valve, and the second side fairing-housing accommodating a turnaround side of the cooler matrix.

13. The gas turbine engine as defined in claim 6 , wherein respective outer skins of each of the first side fairing-housing and the second side fairing-housings extend outwardly at a chamfered angle with respect to a line perpendicular to an outer surface of the cooler matrix, the chamfered angle varying axially from a cooler leading edge to a cooler trailing edge.

Assignees

• Pratt & Whitney Canada

Inventors

• Marini Remo
• Marrano Roberto
• Trumpour Adam

Classifications

• Y02T50/671

  Cross-Sectional Technologies · mapped topic

• F05D2250/50

  Inlet or outlet · CPC title

• F28D2021/0026

  for combustion engines, e.g. for gas turbines or for Stirling engines · CPC title

• F02K1/822

  Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors · CPC title

• F05D2250/51

  Inlet · CPC title