Cooling systems for gas turbine engines

Patent metadata

Field	Value
Publication number	US-2016333783-A1
Application number	US-201415111997-A
Country	US
Kind code	A1
Filing date	Dec 22, 2014
Priority date	Jan 15, 2014
Publication date	Nov 17, 2016
Grant date	—

Abstract

An air-oil cooler for a gas turbine engine includes an air cooling structure and a lubricant channel. The lubricant channel extends between a lubricant inlet and a lubricant inlet and is bounded by the air cooling structure. The air cooling structure has an arcuate shape for circumferentially spanning a portion of a gas turbine engine core.

First claim

What is claimed is:

1 . An air-oil cooler for a gas turbine engine, comprising:
a lubricant channel extending between a lubricant inlet and a lubricant outlet; and an air cooling structure bounding the lubricant channel, wherein the air cooling structure has an arcuate shape configured for circumferentially spanning at least a portion of a gas turbine engine core.

2 . A cooler as recited in claim 1 , wherein the air cooling structure has an annular shape configured to extend about a circumference of the gas turbine engine.

3 . A cooler as recited in claim 1 , wherein the air cooling structure is a first air cooling structure, and further including a second air cooling structure circumferentially adjacent the first air cooling structure.

4 . A cooler as recited in claim 1 , wherein the lubricant inlet and lubricant outlet are on opposite ends of the air cooling structure.

5 . A cooler as recited in claim 1 , wherein the lubricant inlet and lubricant outlet are on a single end of the air cooling structure.

6 . A cooler as recited in claim 1 , wherein the lubricant channel is a single-pass lubricant channel.

7 . A cooler as recited in claim 1 , wherein the lubricant channel is a dual-pass lubricant channel.

8 . A cooler as recited in claim 1 , wherein the air cooling structure defines a plurality of fins oriented obliquely with respect to the lubricant channel.

9 . A cooler as recited in claim 8 , further including a shroud spanning radially outer ends of the plurality of fins.

10 . A lubrication system for a gas turbine engine, comprising:
a lubricant channel extending between a lubricant inlet and a lubricant outlet; an air cooling structure bounding the lubricant channel, wherein the air cooling structure has an arcuate shape configured for circumferentially spanning at least a portion of a gas turbine engine core; and a bypass channel extending in parallel with the lubricant channel, wherein the air-oil cooler is configured to apportion lubricant flow between the lubricant cooling channel and the bypass channel to maintain lubricant in the cooling channel above a congealing temperature and reduce lubricant pressure drop across the air-oil cooler.

11 . A system as recited in claim 10 , further including a fixed orifice or pressure relief valve fluidly coupling the bypass channel and lubricant channel for apportioning lubricant between the channels.

12 . A system as recited in claim 10 , wherein the lubricant channel includes fins for transferring heat from lubricant traversing the lubricant channel.

13 . A system as recited in claim 10 , wherein the bypass channel is a decongeal channel configured for warming oil in the lubricant channel using heat from the gas turbine engine.

14 . A system as recited in claim 10 , wherein the air-oil cooler is a first air-oil cooler and further including a second air-oil cooler circumferentially adjacent to the first air-oil cooler.

15 . A gas turbine engine, comprising:
a lubricant circuit, including:
a bearing compartment;
a lubricant channel in fluid communication with the bearing compartment, wherein the lubricant channel extends between a lubricant inlet a lubricant outlet; and
an air cooling structure bounding the lubricant channel, wherein the air cooling structure has an arcuate shape circumferentially spanning a gas turbine engine core; and
an air diverter in fluid communication with the heat exchanger and configured for reducing drag associated with airflow across the air cooling structure.

16 . An engine as recited in claim 15 , wherein the air diverter includes a nozzle flap operably connected to a synchronization ring for movement between a first position and a second position, wherein the nozzle flap is configured to provide a greater flow of air to the air-oil cooler in the first position than in the second position.

17 . An engine as recited in claim 16 , wherein the synchronization ring couples to an end of the nozzle flap and is configured for displacing the nozzle flap radially with respect to an engine axis of the engine by rotating about a core of the gas turbine engine.

18 . An engine as recited in claim 16 , further including a link coupling the synchronization ring to an aft end of the nozzle flap.

19 . An engine as recited in claim 16 , further including a link coupling the synchronization ring to a forward end of the nozzle flap.

20 . An engine as recited in claim 16 , wherein the synchronization ring spans the circumference of the engine core.

Assignees

• United Technologies Corp

Inventors

• Weiner Richard Alan

Classifications

• F05D2270/66

  Mechanical actuators (F05D2270/62 takes precedence) · CPC title

• F05D2260/22141

  using fins or ribs · CPC title

• F05D2250/90

  Variable geometry · CPC title

• F05D2260/50

  Kinematic linkage, i.e. transmission of position · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title