Turbine disk interstage seal axial retaining ring

• US 5,338,154 A
• Filed: 03/17/1993
• Issued: 08/16/1994
• Est. Priority Date: 03/17/1993
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Albrecht, Richard W., Meade, Robert J., Weisgerber, Robert H.
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): Lee, Michael S.
• Application Number:
  US08/032,214
• Time in Patent Office: 517 Days
• Field of Search: 415/199.5, 415/173.7, 415/174.5, 416/198 A, 416/220 R, 403/351, 403/371
• US Class Current: 415/173.7
• CPC Class Codes: F01D 11/001 for sealing space between stator blade and rotor
• CPC Class Codes: F01D 11/005 Sealing means between non relatively rotating elements
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 403/7058 Split or slotted bushing

Abstract

An axial retention system for an interstage seal located in a gas turbine engine of a type having a turbine section including a first stage disk and a second stage disk. The interstage seal includes a web portion having an aft arm extending from said web, the aft arm having a peripheral rim adjacent the second stage disk. The axial retention system comprising a split ring having two overlapping ends and a plurality of radially outwardly extending tabs for engaging a plurality of inwardly extending tabs located on the second stage disk adjacent the peripheral rim, in a bayonet connection. The retaining ring is located within a slot formed in the peripheral rim and the outwardly extending tabs are positioned in a passageway formed by the disk tabs.

Claims

1. In a turbine engine of a type having a turbine section including first and second stage disks, an interstage seal located between said disks, said seal including a web portion having an aft arm extending from said web and having a peripheral rim adjacent said second stage disk, an interstage seal aft arm axial retention system comprising:

a peripheral groove located in said peripheral rim;

a plurality of tabs located on said second stage disk extending radially inwardly adjacent said peripheral rim;

means located in said groove for forming a bayonet connection with said second stage disk tabs, wherein said bayonet connection means includes a split retaining ring having two ends and a plurality of radially outwardly extending tabs; and

means for preventing circumferential rotation of said axial retention system, wherein said circumferential prevention means is a turbine blade.

2. In a turbine engine of a type having a turbine section including first and second stage disks, an interstage seal located between said disks, said seal including a web portion having an aft arm extending from said web and having a peripheral rim adjacent said second stage disk, an interstage seal aft arm axial retention system comprising:

a peripheral groove located in said peripheral rim;

a plurality of tabs located on said second stage disk extending radially inwardly adjacent said peripheral rim; and

means located in said groove for forming a bayonet connection with said second stage disk tabs;

wherein said bayonet connection means includes a split retaining ring having two ends and a plurality of radially outwardly extending tabs;

wherein said two ends overlap.

3. An apparatus for axially retaining an aft arm of an interstage seal with respect to a second stage turbine disk in a jet turbine engine, said aft arm having a peripheral rim adjacent said second stage disk, said second stage disk having a plurality of radially inwardly extending tabs adjacent said peripheral rim, wherein said apparatus comprises a split retaining ring having two ends and a plurality of radially-outwardly extending tabs for engaging said second stage disk tabs in a bayonet locking connection;

wherein said two ends overlap.

4. The apparatus of claim 3 wherein said split retaining ring is located in a peripheral groove formed in said peripheral rim.