Integrally bladed rotor with slotted outer rim

Patent metadata

Field	Value
Publication number	US-9273563-B2
Application number	US-201213585068-A
Country	US
Kind code	B2
Filing date	Aug 14, 2012
Priority date	Dec 28, 2007
Publication date	Mar 1, 2016
Grant date	Mar 1, 2016

Abstract

An integrally bladed rotor has an outer rim with a plurality of blades extending radially outwardly of the outer rim. A plurality of channels are formed radially inwardly of the outer rim. A discontinuity formed at a radially outer surface of the outer rim includes a first thin slot at a radially outer face of the outer rim with an enlarged seal holding area. A second thin slot is positioned radially inwardly of the seal holding. The first and second thin slots are thinner circumferentially than the enlarged seal holding area. A seal is inserted into the seal holding area. The seal does not extend into the first and second thin slots, nor into the channels.

First claim

What is claimed is:

1. An integrally bladed rotor comprising:
an outer rim having a plurality of blades extending radially outwardly of said outer rim;
a plurality of channels being formed radially inwardly of said outer rim; and
a discontinuity formed at a radially outer surface of said outer rim, including a first thin slot at a radially outer face of said outer rim with an enlarged seal holding area, a second thin slot positioned radially inwardly of said enlarged seal holding area, said first and second thin slots being thinner circumferentially than said enlarged seal holding area, and a seal inserted into said enlarged seal holding area, said seal not extending into said first and second thin slots and said seal not extending into said channels.

2. The integrally bladed rotor as set forth in claim 1 , wherein there are a plurality of discontinuities formed between said blades.

3. The integrally bladed rotor as set forth in claim 1 , wherein said discontinuity is formed non-parallel to a blade stacking line of said blades.

4. The integrally bladed rotor as set forth in claim 1 , wherein said discontinuity is formed non-parallel to a central axis of said integrally bladed rotor.

5. The integrally bladed rotor as set forth in claim 1 , wherein said discontinuity is formed such that it shields a leading edge of one of said blades and a trailing edge of the adjacent blade.

6. The integrally bladed rotor as set forth in claim 1 , wherein said channels are formed non-parallel to a blade stacking line of said blades.

7. The integrally bladed rotor as set forth in claim 1 , wherein said channels are formed non-parallel to a central axis of said integrally bladed rotor.

8. The integrally bladed rotor as set forth in claim 1 , wherein said channels are formed radially inward of a location of said blades.

9. The integrally bladed rotor as set forth in claim 1 , wherein said channels include a first essentially flat portion on a radially inward side of said channel, and a second essentially flat portion on a radially outward side of said channel.

10. A gas turbine engine comprising:
a compressor section including at least one integrally bladed rotor having a plurality of blades, said blades not being parallel to a central axis of said integrally bladed rotor;
said compressor for delivering compressed air downstream into a combustion section, said combustion section for delivering products of combustion downstream across a turbine rotor; and
said integrally bladed rotor of said compression section including
an outer rim having a plurality of blades extending radially outwardly of said outer rim;
a plurality of channels being formed radially inwardly of said outer rim; and
a discontinuity being formed at a radially outer surface of said outer rim, including a first thin slot at a radially outer face of said outer rim with an enlarged seal holding area, a second thin slot positioned radially inwardly of said enlarged seal holding area, said first and second thin slots being thinner circumferentially than said enlarged seal holding area, and a seal inserted into said enlarged seal holding area, said seal not extending into said first and second thin slots and said seal not extending into said channels.

11. The gas turbine engine as set forth in claim 10 , wherein there are a plurality of discontinuities formed between said blades.

12. The gas turbine engine as set forth in claim 10 , wherein said discontinuity is formed non-parallel to a blade stacking line of said blades.

13. The gas turbine engine as set forth in claim 10 , wherein said discontinuity is formed non-parallel to a central axis of said integrally bladed rotor.

14. The gas turbine engine as set forth in claim 10 , wherein said discontinuity is formed such that it shields a leading edge of one of said blades and a trailing edge of the adjacent blade.

15. The gas turbine engine as set forth in claim 10 , wherein said channels are formed non-parallel to a blade stacking line of said blades.

16. The gas turbine engine as set forth in claim 10 , wherein said channels are formed non-parallel to a central axis of said integrally bladed rotor.

17. The gas turbine engine as set forth in claim 10 , wherein said channels are formed radially inward of locations of a leading edge of said blades and a trailing edge of said blades.

18. The gas turbine engine as set forth in claim 10 , wherein said channels include a first essentially flat portion on a radially inward side of said channel, and a second essentially flat portion on a radially outward side of said channel.

19. An integrally bladed rotor comprising:
an outer rim having a plurality of blades extending radially outwardly of said outer rim;
a plurality of channels being formed radially inwardly of said outer rim;
a plurality of discontinuities formed at a radially outer surface of said outer rim and between said blades, each, including a first thin slot at a radially outer face of said outer rim with an enlarged seal holding area, a second thin slot positioned radially inwardly of said enlarged seal holding area, said first and second thin slots being thinner circumferentially than said enlarged seal holding area, and a seal inserted into said enlarged seal holding area, said seal not extending into said first and second thin slots and said seal not extending into said channels;
said discontinuities being formed non-parallel to a blade stacking line of said blades;
said discontinuities being formed non-parallel to a central axis of said integrally bladed rotor;
said channels formed non-parallel to a blade stacking line of said blades;
said channels formed non-parallel to a central axis of said integrally bladed rotor; and
said channels including a first essentially flat portion on a radially inward side of said channel, and a second essentially flat portion on a radially outward side of said channel.

Assignees

• Suciu Gabriel L
• Norris James W
• United Technologies Corp

Inventors

• Suciu Gabriel L
• Norris James W

Classifications

• F05D2260/941

  particularly aimed at mechanical or thermal stress reduction · CPC title

• F04D29/321

  for axial flow compressors · CPC title

• Y02T50/676

  Cross-Sectional Technologies · mapped topic

• Y02T50/671

  Cross-Sectional Technologies · mapped topic

• F04D29/329

  Details of the hub · CPC title