Gas-turbine engine with oil cooler in the engine cowling

Patent metadata

Field	Value
Publication number	US-10082079-B2
Application number	US-201615047286-A
Country	US
Kind code	B2
Filing date	Feb 18, 2016
Priority date	Feb 23, 2015
Publication date	Sep 25, 2018
Grant date	Sep 25, 2018

Abstract

An engine cowling of an aircraft gas-turbine engine with a core engine and a bypass duct surrounding the latter, with a front cowling enclosing the bypass duct and a rear cowling movable in the axial direction, and with stator vanes arranged in the bypass duct, where recesses for removing fluid from the bypass duct are provided in the area of the stator vanes on the inside of the front cowling, where the fluid discharged through the recesses is routed by means of flow ducts through the front cowling, brought into contact with at least one heat exchanger, and subsequently discharged to the environment.

First claim

What is claimed is:

1. An aircraft gas-turbine engine, comprising:
a core engine;
a bypass duct surrounding the core engine;
a front cowling enclosing the bypass duct;
a rear cowling movable in an axial direction;
stator vanes arranged in the bypass duct;
recesses for removing fluid from the bypass duct, the recesses being provided in an area around the stator vanes on an inside of the front cowling;
flow ducts through the front cowling for routing the fluid removed from the bypass duct through the recesses;
a first heat exchanger, wherein the fluid routed by the flow ducts is brought into contact with the first heat exchanger and subsequently discharged to an external environment;
wherein the first heat exchanger is arranged in a forward area of the front cowling;
wherein the fluid is routed into the forward area via vanes of a thrust reversing cascade element.

2. The aircraft gas-turbine engine in accordance with claim 1 , further comprising a second heat exchanger arranged in a vicinity of a gap between the front cowling and the rear cowling.

3. The aircraft gas-turbine engine in accordance with claim 2 , wherein the fluid from the bypass duct is also routed past the second heat exchanger, through the vanes of the thrust reversing cascade element arranged in an area between the front cowling and the rear cowling, and discharged through the gap between the front cowling and the rear cowling.

4. The aircraft gas-turbine engine in accordance with claim 3 , wherein the fluid routed past the first heat exchanger and through the forward area heats the forward area.

5. The aircraft gas-turbine engine in accordance with claim 1 , wherein the fluid routed past the first heat exchanger and through the forward area heats the forward area.

6. The aircraft gas-turbine engine in accordance with claim 2 , wherein the fluid routed past the first heat exchanger and through the forward area heats the forward area.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Todorovic Predrag
• Poenick Sascha

Classifications

• F02K1/72

  the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow · CPC title

• F02K3/06

  with front fan · CPC title

• B64D29/00

  Power-plant nacelles, fairings or cowlings · CPC title

• F05D2260/213

  by the provision of a heat exchanger within the cooling circuit · CPC title

• F01D25/02

  De-icing means for engines having icing phenomena · CPC title