Patent US4239452A successfully refreshed from Google Patents.
US4239452A
Expired / Lapsed
US
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Blade tip shroud for a compression stage of a gas turbine engine
Assignee: RTX Corp
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Filing: 1978-06-26
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Granted: 1980-12-16
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Expires: 1998-06-26
Abstract
Abstract A blade tip shroud structure for a compression stage of a gas turbine engine is disclosed. Various concepts relating to shroud designs and their influence on blade performance are discussed. In accordance with the teaching contained herein, one shroud geometry includes a circumferentially extending recess in the wall of a case which circumscribes the tips of the blades. A surface at the bottom of the recess has discontinuities therein. The tips of the blades run line on line with the respective wall at the design operating condition of the engine in which the shroud structure is incorporated. In one embodiment axially skewed grooves and circumferentially extending grooves form the surface discontinuities.
Inventors
- 👤 Frank Roberts, Jr.
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 00:15
CPC Classifications
F; F01; F01D; F01D11/00; F01D11/08; F01D11/12; F04; F04D; F04D29/00; F04D29/40; F04D29/52; F04D29/522; F04D29/526; F04D29/66; F04D29/68; F04D29/681; F04D29/685
Claims Analysis
Total Claims: 17
Claim 1
Independent Claim
104 words
A compression stage for an axial flow rotary machine, which comprises: a case forming a portion of the outer wall of the flow path for working medium gases of the fan stage; a shroud housed in said fan case and having a first inwardly facing surface, a second inwardly facing surface recessed from said first surface wherein the second surface has a plurality of surface discontinuities formed therein; and a plurality of unshrouded compression blades each having a tip which extends into line on line relationship with the first inwardly facing surface of said shroud at the design operating condition of the compression stage.
Claim 2
Dependent Claim
104 words
A compression stage for an axial flow rotary machine, which comprises: a case forming a portion of the outer wall of the flow path for working medium gases of the fan stage; a shroud housed in said fan case and having a first inwardly facing surface, a second inwardly facing surface recessed from said first surface wherein the second surface has a plurality of surface discontinuities formed therein; and a plurality of unshrouded compression blades each having a tip which extends into line on line relationship with the first inwardly facing surface of said shroud at the design operating condition of the compression stage.
Claim 3
Dependent Claim
20 words
The apparatus according to claim 1 wherein said compression stage is the fan stage of a turbofan, gas turbine engine.
Claim 4
Dependent Claim
70 words
The apparatus according to claim 2 wherein each of said blades has a platform at the base thereof and wherein each blade has a span length S defined as the distance from the platform to the tip of the blade, the second surface of the shroud being recessed from the first surface of the shroud by a distance D which is approximately two tenths percent (0.2%) of the span length.
Claim 5
Dependent Claim
18 words
The apparatus according to claim 3 wherein the span length of the blades is approximately thirty (30) inches.
Claim 6
Dependent Claim
56 words
The apparatus according to claim 1 wherein said surface discontinuities in said second surface include a plurality of axially extending grooves at the bottom of the recess and wherein the number of grooves in said plurality of grooves exceeds the number of blades in said plurality of blades by at least a factor of two (2).
Claim 7
Dependent Claim
36 words
The apparatus according to claim 5 wherein each of said axially extending grooves is skewed in the direction of machine rotation with respect to a radial line drawn from the axis of rotation of the machine.
Claim 8
Dependent Claim
27 words
The apparatus according to claim 6 wherein said surface discontinuities in said second surface include a plurality of circumferentially extending grooves at the bottom of the recess.
Claim 9
Dependent Claim
27 words
The apparatus according to claim 1 wherein said surface discontinuities in said second surface include a plurality of circumferentially extending grooves at the bottom of the recess.
Claim 10
Dependent Claim
56 words
The apparatus according to claim 2 wherein said surface discontinuites in said second surface include a plurality of axially extending grooves at the bottom of the recess and wherein the number of grooves in said plurality of grooves exceeds the number of blades in said plurality of blades by at least a factor of two (2).
Claim 11
Dependent Claim
36 words
The apparatus according to claim 9 wherein each of said axially extending grooves is skewed in the direction of machine rotation with respect to a radial line drawn from the axis of rotation of the machine.
Claim 12
Dependent Claim
27 words
The apparatus according to claim 10 wherein said surface discontinuities in said second surface include a plurality of circumferentially extending grooves at the bottom of the recess.
Claim 13
Dependent Claim
70 words
The apparatus according to claim 10 wherein each of said blades has a platform at the base thereof and wherein each blade has a span length S defined as the distance from the platform to the tip of the blade, the second surface of the shroud being recessed from the first surface of the shroud by a distance D which is approximately two tenths percent (0.2%) of the span length.
Claim 14
Dependent Claim
18 words
The apparatus according to claim 11 wherein the span length of the blades is approximately thirty (30) inches.
Claim 15
Dependent Claim
27 words
The apparatus according to claim 2 wherein said surface discontinuities in said second surface include a plurality of circumferentially extending grooves at the bottom of the recess.
Claim 16
Dependent Claim
70 words
The apparatus according to claim 14 wherein each of said blades has a platform at the base thereof and wherein each blade has a span length S defined as the distance from the platform to the tip of the blade, the second surface of the shroud being recessed from the first surface of the shroud by a distance D which is approximately two tenths percent (0.2%) of the span length.
Claim 17
Dependent Claim
18 words
The apparatus according to claim 15 wherein the span length of the blades is approximately thirty (30) inches.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1983-12-16 | 1984-06-16 | 1984-12-16 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1987-12-16 | 1988-06-16 | 1988-12-16 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1991-12-16 | 1992-06-16 | 1992-12-16 | $7700.00 | Window Closed / Lapsed |