Protection system and turbo engine with a protection system

Patent metadata

Field	Value
Publication number	US-2016298487-A1
Application number	US-201615094234-A
Country	US
Kind code	A1
Filing date	Apr 8, 2016
Priority date	Apr 10, 2015
Publication date	Oct 13, 2016
Grant date	—

Abstract

A protection system for a turbo engine, in particular an aircraft engine is provided. The turbo engine comprises at least one fluid duct element with a casing device comprising at least one casing section, encasing at least partially the at least one fluid duct element, said casing device comprising at least one fluid escaping means, wherein the casing device is intended to at least partially contain and/or deflect a fluid stemming from a burst event at the fluid duct element event in order to at least partially protect the turbo engine.

First claim

1 . A protection system for a turbo engine, in particular an aircraft engine, said turbo engine comprising at least one fluid duct element, with a casing device comprising at least one casing section, encasing at least partially the at least one fluid duct element, said casing device comprising at least one fluid escaping means, wherein the casing device is intended to at least partially contain and/or deflect a fluid stemming from a burst event at the fluid duct element in order to at least partially protect the turbo engine.

2 . The protection system according to claim 1 , wherein the casing device comprises at least one opening being provided as fluid escaping means.

3 . The protection system according to claim 1 , wherein the casing device comprises at least one deflection and/or shielding means.

4 . The protection system according to claim 1 , wherein the casing device comprises several casing sections being at least partially in fluid communication, wherein at least one fluid escaping means is provided at a transition point between at least two casing sections.

5 . The protection system according to claim 4 , wherein the spatial distance between at least two casing sections is adjustable.

6 . The protection system according to claim 4 , wherein the several casing sections comprise at least one deflection and/or shielding means at a transition point providing fluid escaping means.

7 . The protection system according to claim 3 , wherein disc shaped elements are provided as deflection and/or shielding means.

8 . The protection system according to claim 1 , wherein the casing device comprises at least one flexible sleeve as a casing section and/or a rigid casing section.

9 . The protection system according to claim 1 , wherein the casing device is provided to at least partially protect the region surrounding the casing device from debris produced by a burst event at the fluid duct element being at least partially encased by the casing device.

10 . The protection system according to claim 1 , wherein the casing device is provided to maintain at least partially the flow of fluid of a burst fluid duct element being at least partially encased by the casing device.

11 . The protection system according to claim 1 , wherein the casing device is provided to deflect the outflow of escaping fluid of a burst fluid duct element being at least partially encased by the casing device in radial direction seen from the axis of the casing device.

12 . The protection system according to claim 1 , wherein the fluid duct element comprises a cooling pipe.

13 . The protection system according to claim 1 , wherein the location of the at least one fluid escaping means is adjustable.

14 . The protection system according to claim 1 , wherein the direction of the flow of escaping fluid is adjustable.

15 . A turbo engine, in particular an aircraft turbo engine comprising at least one protection system according to claim 1 .

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Teia Dos Santos Mendes Gomes Luis Daniel

Classifications

• F01D25/12

  Cooling · CPC title

• F01D21/14 Primary

  responsive to other specific conditions · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F01D25/14

  Casings modified therefor (double casings F01D25/26) · CPC title

• F01D25/26

  Double casings; Measures against temperature strain in casings · CPC title