Impingement baffle for a gas turbine engine and gas turbine engine

Patent metadata

Field	Value
Publication number	US-9988922-B2
Application number	US-88326010-A
Country	US
Kind code	B2
Filing date	Sep 16, 2010
Priority date	Sep 17, 2009
Publication date	Jun 5, 2018
Grant date	Jun 5, 2018

Abstract

An impingement baffle for a gas turbine engine is provided. The impingement baffle is a one piece impingement ring with one opening and with fastening elements at both free ends of the impingement ring to enable the closing of the impingement ring. A gas turbine engine including at least one such an impingement baffle is also provided.

First claim

The invention claimed is:

1. An impingement baffle for a gas turbine engine, comprising:
a fastening element at both of two free ends,
wherein the impingement baffle is a one piece impingement ring, the one piece impingement ring being a split ring that is split at a single location, and
wherein the fastening element enables the closing of the impingement ring,
wherein a first fastening element comprises a male connection flap and a second fastening element comprises a female connection flap, and
wherein the male connection flap and the female connection flap are arranged at a first free end of the impingement ring and overlap with complementary connection flaps arranged at a second free end of the impingement ring.

2. The impingement baffle as claimed in claim 1 , wherein the impingement ring is elastic.

3. The impingement baffle as claimed in claim 2 , wherein the impingement ring is spring-elastic.

4. The impingement baffle as claimed in claim 1 , wherein the fastening elements comprise a locking device for assembling the fastening elements of both of two free ends to each other.

5. The impingement baffle as claimed in claim 4 , wherein the locking device is a hook at a first fastening element at a first free end and a recess for engaging the hook at a second fastening element at a second free end.

6. The impingement baffle as claimed in claim 1 , wherein each fastening element comprises an elongated beam whereby the elongated beam of each free end is arranged parallel and displaced to each other.

7. The impingement baffle as claimed in claim 6 ,
wherein the male connection flap is located at a first free end of the elongated beam of the first fastening element, and
wherein the female connection flap is located in an area where the elongated beam arises from a main body of the impingement ring.

8. The impingement baffle as claimed in claim 6 , wherein the elongated beam of the first fastening element of the first free end may be slid on the elongated beam of the second fastening element of the second free end.

9. The impingement baffle as claimed in claim 1 , wherein the impingement ring comprises a plurality of holes.

10. The impingement baffle as claimed in claim 1 , wherein impingement ring is laser manufactured, and wherein the fastening elements of the impingement ring are laser manufactured.

11. The impingement baffle as claimed in claim 1 , wherein fastening elements are each aligned along the respective free ends of the impingement ring such that once the impingement ring is closed it has a cylindrical inner surface without any elevation.

12. The impingement baffle as claimed in claim 1 , wherein at each free end of the impingement ring at least a male and at least a female connection flaps are arranged.

13. The impingement baffle for a gas turbine engine as claimed in claim 1 wherein the fastening element of the first free end can slide on the fastening element of the second free end.

14. A gas turbine engine, comprising:
an impingement baffle, comprising:
a fastening element at both of two free ends,

wherein the impingement baffle is a one piece impingement ring, the one piece impingement ring being a split ring that is split at a single location, and
wherein the fastening element enables the closing of the impingement ring,
wherein a first fastening element comprises a male connection flap and a second fastening element comprises a female connection flap, and
wherein the male connection flap and the female connection flap are arranged at a first free end of the impingement ring and overlap with complementary connection flaps arranged at a second free end of the impingement ring.

15. The gas turbine as claimed in claim 14 , wherein the impingement ring is elastic.

16. The gas turbine as claimed in claim 15 , wherein the impingement ring is spring-elastic.

17. The gas turbine engine as claimed in claim 14 wherein the fastening element of the first free end can slide on the fastening element of the second free end.

Assignees

• Friis Johan
• Siemens Ag

Inventors

• Friis Johan

Classifications

• F01D25/12

  Cooling · CPC title

• F05D2230/13

  using lasers · CPC title

• F01D11/08 Primary

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title