Gas turbine engine anti-icing system

Patent metadata

Field	Value
Publication number	US-9945247-B2
Application number	US-201514813755-A
Country	US
Kind code	B2
Filing date	Jul 30, 2015
Priority date	Aug 26, 2014
Publication date	Apr 17, 2018
Grant date	Apr 17, 2018

Abstract

An anti-icing system for an engine section stator of a gas turbine engine. The system includes an environmental control system pre-cooler heat exchange system and a conduit. The environmental control system pre-cooler heat exchange system is configured to exchange heat between air bled from a compressor of the engine and bypass duct air. The conduit is configured to exchange heat from the pre-cooler heat exchange system to a heat transfer medium. The conduit is also configured to transfer the heat from the heat transfer medium to the engine section stator.

First claim

The invention claimed is:

1. A gas turbine engine comprising an anti-icing system for a compressor stator of the gas turbine engine, the anti-icing system comprising:
an environmental control pre-cooler heat exchange system configured to:
exchange heat between air bled from a compressor of the gas turbine engine and bypass duct air, and
exchange heat from the bypass air heated by the air bled from the compressor to a heat transfer medium located within a conduit, the conduit extending from the environmental control system pre-cooler heat exchange system to the compressor stator and being configured to transfer heat from the heat transfer medium to the compressor stator,

wherein the conduit extends through an outlet guide vane for a bypass duct of the gas turbine engine.

2. The gas turbine engine according to claim 1 , wherein the environmental control pre-cooler heat exchange system comprises a heat exchanger configured to transfer heat from the air bled from the compressor to the bypass duct air and to the further heat transfer medium.

3. The gas turbine engine according to claim 1 , wherein the environmental control pre-cooler heat exchange system comprises a first heat exchanger configured to transfer heat from the air bled from the compressor to the bypass duct air, and a second heat exchanger configured to transfer heat from the bypass duct air heated by the first heat exchanger to the further heat transfer medium.

4. The gas turbine engine according to claim 1 , wherein the gas turbine engine comprises a multi-spool gas turbine engine.

5. The gas turbine engine according to claim 1 , wherein the heat transfer medium comprises a heat transfer fluid, and the anti-icing system is configured to circulate the heat transfer fluid between the environmental control pre-cooler heat exchange system and the compressor stator.

6. The gas turbine engine according to claim 5 , wherein the anti-icing system comprises a pump configured to circulate the heat transfer fluid within the conduit, wherein the heat transfer fluid is configured to flow in a closed loop.

7. The gas turbine engine according to claim 5 , wherein the conduit comprises a heat pipe.

8. The gas turbine engine according to claim 1 , wherein the anti-icing system is configured to further transfer the heat within the heat transfer medium to a fan root of the gas turbine engine.

9. The gas turbine engine according to claim 8 , wherein the conduit extends into the fan root to transfer the heat within the heat transfer medium to the fan root.

10. The gas turbine engine according to claim 1 , further comprising:
a bypass passage for the bypass air, the bypass passage extending from the bypass duct and through the environmental control pre-cooler heat exchange system; and
a bleed passage for the air bled from the compressor, the bleed passage extending from the compressor to the environmental control pre-cooler heat exchange system, wherein
the environmental control pre-cooler heat exchange system is configured to exchange heat from the bleed passage to the bypass passage and to exchange heat from the bypass passage to the conduit.

11. The gas turbine engine according to claim 10 , wherein the conduit extends through the compressor stator and into a fan root of the gas turbine engine, the anti-icing system being configured to further transfer heat to the fan root.

12. The gas turbine engine according to claim 10 , wherein the environmental control pre-cooler heat exchange system further comprises a first heat exchanger and a second heat exchanger, wherein the bleed passage and the bypass passage exchange heat in the first heat exchanger and the bypass passage and the conduit exchange heat in the second heat exchanger.

Assignees

• Rolls Royce Plc

Inventors

• Appukuttan Ajith
• Keeler Benjamin
• Vanacore Paolo

Classifications

• F01D25/10

  Heating, e.g. warming-up before starting · CPC title

• F02C7/141

  of working fluid · CPC title

• F01D17/105

  by passing part of the fluid · CPC title

• F05D2240/10

  Stators · CPC title

• B64D2013/0607

  providing hot air or liquid for deicing aircraft parts, e.g. aerodynamic surfaces or windows · CPC title