Patent US5156529A successfully refreshed from Google Patents.
US5156529A
Expired / Lapsed
US
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Integral shroud blade design
Assignee: Siemens Energy Inc
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Filing: 1991-03-28
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Granted: 1992-10-20
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Expires: 2011-03-28
Abstract
Abstract An integral shroud blade comprising a root portion for mounting the blade in a row on a turbine rotor; a platform portion; an airfoil portion extending upwardly from the platform portion and having a leading edge, a trailing edge, and a tip; a shroud formed on the tip of the airfoil portion and having two opposite tangential side surfaces and a top surface; and at least one pair of holes extending into the shroud, each of the two tangential sides having one hole of each pair being formed therein.
Inventors
- 👤 Jurek Ferleger
- 👤 Harry F. Martin
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 05:31
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/12; F01D5/22; F01D5/24; F01D5/14; F01D5/16; F01D5/225; Y; Y10; Y10S; Y10S416/00; Y10S416/50; Y10T; Y10T29/00; Y10T29/49; Y10T29/49316; Y10T29/4932
Claims Analysis
Total Claims: 9
Claim 1
Independent Claim
131 words
An integral shroud blade comprising: a root portion for mounting the blade in a row on a turbine rotor; a platform portion; an airfoil portion extending upwardly from the platform portion and having a leading edge, a trailing edge, and a tip; a shroud formed on the tip of the airfoil position and having two opposite tangential side surfaces and a top surface; and at least one pair of holes extending into the shroud through the tangential sides thereof, one of the holes being formed in one of the tangential sides and the other of the holes being formed in the other of the tangential sides, and wherein the holes of each pair of holes are coaxial and each hole has a different depth from the other hole of each pair.
Claim 2
Dependent Claim
131 words
An integral shroud blade comprising: a root portion for mounting the blade in a row on a turbine rotor; a platform portion; an airfoil portion extending upwardly from the platform portion and having a leading edge, a trailing edge, and a tip; a shroud formed on the tip of the airfoil position and having two opposite tangential side surfaces and a top surface; and at least one pair of holes extending into the shroud through the tangential sides thereof, one of the holes being formed in one of the tangential sides and the other of the holes being formed in the other of the tangential sides, and wherein the holes of each pair of holes are coaxial and each hole has a different depth from the other hole of each pair.
Claim 3
Dependent Claim
123 words
An integral shroud blade as recited in claim 1, wherein the airfoil portion has a convex side surface and a concave side surface, and wherein one of the two opposite tangential side surfaces of the shroud overlies the convex surface of the airfoil portion and the other of the two opposite tangential side surfaces overlies the concave side surface of the airfoil portion, and wherein the hole of each pair of holes formed in the tangential side of the shroud which overlies the concave side surface of the airfoil portion has a depth greater than that of the other hole of each pair of holes which is formed in the tangential side surface which overlies the convex side surface of the airfoil portion.
Claim 4
Dependent Claim
47 words
An integral shroud blade as recited in claim 1, wherein a center of gravity of the shroud is disposed above a centroid of the root portion so as to minimize eccentric stresses during blade rotation, and the shroud is centered in a tangential direction of the blade.
Claim 5
Dependent Claim
150 words
An integral shroud blade comprising: a root portion for mounting the blade in a row on a turbine rotor; a platform portion; an airfoil portion extending upwardly from the platform portion and having a leading edge, a trailing edge, and a tip; a shroud formed on the tip of the airfoil portion and having two opposite tangential side surfaces, a top surface and a rear surface, the rear surface of the shroud substantially overlying the leading edge of the airfoil; and at least one pair of grooves, each groove of each pair of grooves being formed in the rear surface of the shroud, each groove extending from one of the two opposite tangential side surfaces towards each other, the two grooves of each pair of grooves having a length and depth which is selected to place the center of gravity of the shroud above a centroid of the root portion.
Claim 6
Dependent Claim
150 words
An integral shroud blade comprising: a root portion for mounting the blade in a row on a turbine rotor; a platform portion; an airfoil portion extending upwardly from the platform portion and having a leading edge, a trailing edge, and a tip; a shroud formed on the tip of the airfoil portion and having two opposite tangential side surfaces, a top surface and a rear surface, the rear surface of the shroud substantially overlying the leading edge of the airfoil; and at least one pair of grooves, each groove of each pair of grooves being formed in the rear surface of the shroud, each groove extending from one of the two opposite tangential side surfaces towards each other, the two grooves of each pair of grooves having a length and depth which is selected to place the center of gravity of the shroud above a centroid of the root portion.
Claim 7
Dependent Claim
32 words
An integral shroud blade as recited in claim 4, wherein one of the grooves of the pair of grooves has a length longer than the other groove of the pair of grooves.
Claim 8
Independent Claim
175 words
A method of tuning shrouded blades mounted in a row on a rotor of a steam turbine, wherein each blade of the row has a root portion for mounting the blade in the row on the turbine rotor, a platform portion, an airfoil portion extending upwardly from the platform portion and having a leading edge, a trailing edge, and a tip, and a shroud formed on the tip of the airfoil portion and having two opposite tangential side surfaces, a top surface and a rear surface, the method comprising the steps of: forming at least a pair of holes extending into the shroud through the tangential sides thereof, one of the holes being formed in one of the tangential sides and the other of the holes being formed in the other of the tangential sides, and said pair of holes being formed in the shroud of each of the blades of the row; and varying the hole depth between adjacent blades so as to create a minor frequency change for alternating blades of the row.
Claim 9
Independent Claim
175 words
A method of tuning shrouded blades mounted in a row on a rotor of a steam turbine, wherein each blade of the row has a root portion for mounting the blade in the row on the turbine rotor, a platform portion, an airfoil portion extending upwardly from the platform portion and having a leading edge, a trailing edge, and a tip, and a shroud formed on the tip of the airfoil portion and having two opposite tangential side surfaces, a top surface and a rear surface, the method comprising the steps of: forming at least a pair of holes extending into the shroud through the tangential sides thereof, one of the holes being formed in one of the tangential sides and the other of the holes being formed in the other of the tangential sides, and said pair of holes being formed in the shroud of each of the blades of the row; and varying the hole depth between adjacent blades so as to create a minor frequency change for alternating blades of the row.
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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) | 1995-10-20 | 1996-04-20 | 1996-10-20 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1999-10-20 | 2000-04-20 | 2000-10-20 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2003-10-20 | 2004-04-20 | 2004-10-20 | $7700.00 | Window Closed / Lapsed |