Patent US5226785A successfully refreshed from Google Patents.
US5226785A
Expired / Lapsed
US
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Impeller system for a gas turbine engine
Assignee: General Electric Co
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Filing: 1991-10-30
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Granted: 1993-07-13
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Expires: 2011-10-30
Abstract
Abstract An interstage thermal shield assembly for a gas turbine engine. The assembly includes an axially-extending thermal shield positioned between first and second stage disks to form a seal therebetween. The thermal shield includes complementary hook members shaped to engage slotted hook members formed on the first stage disk to form a bayonet connection, and complementary lip members for engaging lobe members formed on the second stage disk by virtue of split rings, thereby eliminating the need for a bolted connection between the thermal shield and disks and facilitating attachment and removal of the thermal shield. The thermal shield includes an annular impeller which is positioned rearwardly of the first stage disk, the impeller including bayonet connection with the disk which restrains the impeller from axial deflection, but permits radial deflection in response to thermal changes. The thermal shield also includes an annular bore, attached to and extending radially inwardly from the thermal shield, and rotating in a plane substantially normal to a rotational axis of the shaft mounting the disks. The bore is shaped to have a center of mass out of the plane of rotation, so that rotation of the bore creates a moment which urges the bore to deflect toward the upstream disk, thereby compensating for a pressure differential across the face of the bore as cooling air is pumped by the impeller radially outwardly toward the end of the first stage disk.
Inventors
- 👤 Anand D. Narayana
- 👤 Richard L. Stanley
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-04 18:22
CPC Classifications
F; F01; F01D; F01D11/00; F01D11/001; F01D5/00; F01D5/02; F01D5/08; F01D5/081; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 14
Claim 1
Independent Claim
100 words
An impeller system for use with a gas turbine engine of a type having a first stage disk mounted on a rotating turbine shaft, the system comprising: annular impeller means positioned rearwardly of said first stage disk about said shaft and including means for securing said impeller means at a base thereof to said disk; and interlocking means, extending between said impeller means and said disk, positioned radially outwardly of said securing means, whereby said impeller is restrained from axial deflection, but permitted radial deflection in response to thermal changes; and wherein said securing means comprises a plurality of bolts.
Claim 2
Dependent Claim
100 words
An impeller system for use with a gas turbine engine of a type having a first stage disk mounted on a rotating turbine shaft, the system comprising: annular impeller means positioned rearwardly of said first stage disk about said shaft and including means for securing said impeller means at a base thereof to said disk; and interlocking means, extending between said impeller means and said disk, positioned radially outwardly of said securing means, whereby said impeller is restrained from axial deflection, but permitted radial deflection in response to thermal changes; and wherein said securing means comprises a plurality of bolts.
Claim 3
Dependent Claim
39 words
The system of claim 1 wherein said impeller means includes a plurality of radially-extending passages extending therethrough, wherein said passages are angled axially forwardly to route cooling air to a plurality of blades attached to said first stage disk.
Claim 4
Dependent Claim
21 words
The system of claim 2 wherein said passages taper outwardly such that cross sectional areas thereof increase in radially outward direction.
Claim 5
Dependent Claim
13 words
The system of claim 1 wherein said interlocking means comprises a bayonet-type mount.
Claim 6
Dependent Claim
43 words
The system of claim 4 wherein said bayonet-type mount includes a plurality of fingers extending rearwardly from and spaced about said first stage disk, and an annular flange extending about a forward face of said impeller means and shaped to receive said fingers.
Claim 7
Dependent Claim
27 words
The impeller of claim 5 wherein said flange includes radially-outwardly extending complementary fingers; and said fingers on said disk are spaced to receive said complementary fingers therebetween.
Claim 8
Dependent Claim
10 words
The system of claim 1 further comprising flow restricting means.
Claim 9
Dependent Claim
37 words
The system of claim 7 wherein said flow restricting means includes an annular ring extending radially from an outer periphery of said impeller means and positioned adjacent to an annular ring formed on an associated thermal shield.
Claim 10
Dependent Claim
101 words
An impeller system for use with a gas turbine engine of a type having a first stage disk mounted on a rotating turbine shaft, the system comprising: annular impeller means positioned rearwardly of said first stage disk about said shaft and including means for securing said impeller means at a base thereof to said disk; and interlocking means, extending between said impeller means and said disk, positioned radially outwardly of said securing means, whereby said impeller is restrained from axial deflection, but permitted radial deflection in response to thermal changes; and wherein said impeller means include first and second disk portions.
Claim 11
Dependent Claim
101 words
An impeller system for use with a gas turbine engine of a type having a first stage disk mounted on a rotating turbine shaft, the system comprising: annular impeller means positioned rearwardly of said first stage disk about said shaft and including means for securing said impeller means at a base thereof to said disk; and interlocking means, extending between said impeller means and said disk, positioned radially outwardly of said securing means, whereby said impeller is restrained from axial deflection, but permitted radial deflection in response to thermal changes; and wherein said impeller means include first and second disk portions.
Claim 12
Dependent Claim
23 words
The system of claim 9 wherein said impeller means includes dividers extending between said disk portions, said disks and dividers forming said passages.
Claim 13
Dependent Claim
93 words
In a gas turbine engine having first and second stage disk means for mounting turbine blades, an annular thermal shield connecting said disk means, and disk-shaped impeller means, bolted adjacent a radially inner periphery thereof to a base of said first stage disk means, the improvement comprising: said first stage disk means and said impeller means having interlocking means extending therebetween and located adjacent a periphery of said impeller for restraining deflection of said impeller means in an axial direction, but permitting radial expansion of said impeller means in response to thermal changes.
Claim 14
Dependent Claim
93 words
In a gas turbine engine having first and second stage disk means for mounting turbine blades, an annular thermal shield connecting said disk means, and disk-shaped impeller means, bolted adjacent a radially inner periphery thereof to a base of said first stage disk means, the improvement comprising: said first stage disk means and said impeller means having interlocking means extending therebetween and located adjacent a periphery of said impeller for restraining deflection of said impeller means in an axial direction, but permitting radial expansion of said impeller means in response to thermal changes.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1996-07-12 | 1997-01-11 | 1997-07-13 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2000-07-12 | 2001-01-11 | 2001-07-13 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2004-07-12 | 2005-01-11 | 2005-07-13 | $7700.00 | Window Closed / Lapsed |