Dual filtration particle separator

Patent metadata

Field	Value
Publication number	US-9982599-B2
Application number	US-201314443145-A
Country	US
Kind code	B2
Filing date	Jun 20, 2013
Priority date	Dec 10, 2012
Publication date	May 29, 2018
Grant date	May 29, 2018

Abstract

A gas turbine engine has a first particle separator stage including a surface for impacting air at outer periphery of an air flow passage, capturing impacted particles at the outer periphery, and routing captured particles towards a second particle separator stage. Air inward of the first particle separator stage passes towards a core of the engine. Cleaner air upstream of the second particle separator stage is utilized for an air function at a location other than the core engine. A particle discharge is disposed downstream of said second particle separator stage.

First claim

The invention claimed is:

1. A gas turbine engine comprising:
a first particle separator stage including a surface for:
impacting air at an outer periphery of an air flow passage capturing impacted particles at said outer periphery,
delivering cleaner air into a core engine through a path; and

whereby:
air inward of the first particle separator stage passes towards a core of said engine, and
cleaner air upstream of the second particle separator stage is utilized for an air function at a location other than the core engine, and

a particle discharge is disposed downstream of said second particle separator stage,
wherein a ring provides said first particle separator stage, and extends circumferentially to direct separated particles towards the second particle separator stage, and
wherein said particle separator surrounds a nose cone, with said path into said core engine downstream and radially inwardly of said surface, and outwardly of said nose cone, and said first stage particle separator including a chamber to gather and force particles around a periphery of said first stage particle separator to gather in a location that will be vertically lower in said first stage particle separator.

2. The gas turbine engine as set forth in claim 1 , wherein said second particle separator stage is generally located at a location spaced by 180° from a mount surface for an associated gas turbine engine.

3. The gas turbine engine as set forth in claim 1 , wherein said cleaner air for said air function passing over an air oil cooler heat exchanger.

4. The gas turbine engine as set forth in claim 1 , wherein said cleaner air for said air function passing over an air oil cooler heat exchanger.

5. The gas turbine engine as set forth in claim 4 , wherein said particle separator surrounds a nose cone, with a path into said core engine being downstream and radially inwardly of said surface, and outwardly of the surface of said nose cone.

6. The gas turbine engine as set forth in claim 1 , wherein said particle separator surrounds a nose cone, with a path into said core engine being downstream and radially inwardly of said surface, and outwardly of the surface of said nose cone.

7. A gas turbine engine as set forth in claim 1 , wherein said core engine includes a turbine section, a compressor section and a propulsor section, with there being at least two turbine rotors in said turbine section and a first and second compressor rotor, and a propulsor, with said at least two turbine rotors each driving one of said first and second compressor rotors, and said propulsor not being driven at the same speed as either of said first and second turbine rotors.

8. The gas turbine engine as set forth in claim 7 , wherein said propulsor is driven by one of said first and second turbine rotors which is driving a lower stage one of said first and second compressor rotors, and there being a gear reduction between said one of said first and second turbine rotors and said propulsor.

9. The gas turbine engine as set forth in claim 7 , wherein said propulsor is driven by a third propulsor turbine rotor, which is positioned to be downstream of said at least two turbine rotors.

10. The gas turbine engine as set forth in claim 7 , wherein said second compressor rotor is downstream of said first compressor rotor, and said second compressor rotor having a first overall pressure ratio and said first compressor rotor having a second overall pressure ratio, and a ratio of said first overall pressure ratio to said second overall pressure ratio being greater than or equal to about 2.0.

11. The gas turbine engine as set forth in claim 10 , wherein said ratio of said first overall pressure ratio to said second overall pressure ratio is greater than or equal to about 3.0.

12. The gas turbine engine as set forth in claim 11 , wherein said ratio of said first overall pressure ratio to said second overall pressure ratio is greater than or equal to about 3.5.

13. The gas turbine engine as set forth in claim 12 , wherein said ratio of said first overall pressure ratio to said second overall pressure ratio being less than or equal to about 8.0.

14. The gas turbine engine as set forth in claim 8 , wherein the propulsor turbine drives a fan at an upstream end of the engine.

15. The gas turbine engine as set forth in claim 4 , wherein said ratio of said first overall pressure ratio to said second overall pressure ratio being less than or equal to about 8.0.

16. The gas turbine engine as set forth in claim 7 , wherein the propulsor turbine drives a fan at an upstream end of the engine.

17. The gas turbine engine as set forth in claim 7 , wherein an axially outer position is defined by said fan, and said propulsor turbine being positioned between said fan and said first and second turbine rotors, and said first and second compressor rotors being positioned further into said engine relative to said first and second turbine rotors.

18. The gas turbine engine as set forth in claim 7 , wherein said propulsor is a plurality of propellers.

Assignees

• United Technologies Corp

Inventors

• Suciu Gabriel L
• Chandler Jesse M

Classifications

• F02C7/052 Primary

  with dust-separation devices · CPC title

• F02C7/12

  Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P) · CPC title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• F05D2260/607

  Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles · CPC title

• F05D2220/327

  to drive shrouded, high solidity propeller · CPC title