US4247247A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Blade tip clearance control
Assignee: Rolls Royce Corp
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Filing: 1979-05-29
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Granted: 1981-01-27
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Expires: 1999-05-29
Abstract
Abstract A turbine blade tip seal assembly for controlling the blade tip clearance between a flexible outer shroud and the tips of a thermally expansible row of turbine blades on a turbine rotor includes a fixed outer shroud with a pressure deflectable wall portion thereon located in surrounding, radially outwardly relationship with blade tips on the blades of a turbine rotor and wherein an excessive blade tip to shroud wall spacing is maintained when the engine is at cold start conditions; said turbine blades of the turbine rotor expanding in response to increases in operating temperature within the engine during turbine engine operation to partially close the excessive blade tip to shroud clearance and further including pressurizable means responsive to turbine operation to produce pressure bias on the deflectable wall to cause it to be deflected raidally inwardly to further reduce the excessive blade tip clearance so as to produce a resultant operative clearance between the tip of the turbine rotor and the shroud to prevent excessive gas bypass between the wall and the blade tips; said pressurizable means including a secondary pressurizable chamber responsive to engine operating conditions to apply a secondary pressure on the wall to produce a fine-tuned adjustment of the blade tip clearances between leading and trailing edges of the blades when the engine has reached an elevated equilibrium temperature of operation.
Inventors
- 👤 Glenn W. Thebert
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 12:07
CPC Classifications
F; F01; F01D; F01D11/00; F01D11/08; F01D11/14; F01D11/20; F01D11/22
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
120 words
A turbine blade tip seal assembly for use in controlling blade tip gas bypass as motive fluid is directed across a turbine blade row comprising: a fixed outer shroud with a deflectable wall, turbine rotor having blades thereon with tips located in spaced relationship to said deflectable wall, means forming a first pressurizable chamber inflatable to a predetermined pressure to deflect said deflectable wall radially inwardly into a controlled radial clearance with said tips to prevent excessive gas bypass between said wall and said blade tips, and means including a secondary pressurizable chamber responsive to engine operating conditions to apply a secondary pressure on said wall to produce a further adjustment of said clearance in accordance with engine operating conditions.
Claim 2
Dependent Claim
120 words
A turbine blade tip seal assembly for use in controlling blade tip gas bypass as motive fluid is directed across a turbine blade row comprising: a fixed outer shroud with a deflectable wall, turbine rotor having blades thereon with tips located in spaced relationship to said deflectable wall, means forming a first pressurizable chamber inflatable to a predetermined pressure to deflect said deflectable wall radially inwardly into a controlled radial clearance with said tips to prevent excessive gas bypass between said wall and said blade tips, and means including a secondary pressurizable chamber responsive to engine operating conditions to apply a secondary pressure on said wall to produce a further adjustment of said clearance in accordance with engine operating conditions.
Claim 3
Dependent Claim
180 words
A turbine blade tip seal assembly for use in controlling blade tip gas bypass as motive fluid is directed across a turbine blade row comprising; a fixed outer shroud with a deflectable wall, a turbine rotor having blades thereon with tips located in spaced relationship to said deflectable wall, means forming a first pressurizable chamber inflatable to a predetermined pressure to deflect said deflectable wall radially inwardly into a controlled radial clearance with said tips to prevent excessive gas bypass between said wall and said blade tips, and means including a secondary pressurizable chamber responsive to engine operating conditions to apply a secondary pressure on said wall to produce a further adjustment of said clearance in accordance with engine operating conditions, said outer shroud having axially spaced rigid end segments and an outer wall defining an annular cavity, said deflectable wall being spaced from said outer wall and defining the inner surface of said outer shroud and the inner wall of the cavity thereby to define said first pressurizable chamber, said last mentioned means being located within said first cavity.
Claim 4
Dependent Claim
180 words
A turbine blade tip seal assembly for use in controlling blade tip gas bypass as motive fluid is directed across a turbine blade row comprising; a fixed outer shroud with a deflectable wall, a turbine rotor having blades thereon with tips located in spaced relationship to said deflectable wall, means forming a first pressurizable chamber inflatable to a predetermined pressure to deflect said deflectable wall radially inwardly into a controlled radial clearance with said tips to prevent excessive gas bypass between said wall and said blade tips, and means including a secondary pressurizable chamber responsive to engine operating conditions to apply a secondary pressure on said wall to produce a further adjustment of said clearance in accordance with engine operating conditions, said outer shroud having axially spaced rigid end segments and an outer wall defining an annular cavity, said deflectable wall being spaced from said outer wall and defining the inner surface of said outer shroud and the inner wall of the cavity thereby to define said first pressurizable chamber, said last mentioned means being located within said first cavity.
Claim 5
Dependent Claim
190 words
A turbine blade tip seal assembly for use in controlling blade tip gas bypass as motive fluid is directed across a turbine blade row comprising: a fixed outer shroud with a deflectable wall turbine rotor having blades thereon with tips located in close spaced relationship to said deflectable wall and including leading and trailing edges, means forming a first pressurizable chamber inflatable to a predetermined pressure to deflect said wall radially inwardly into a controlled radial clearance with said tips to prevent excessive gas bypass between said wall and said blade tips and means including a secondary pressurizable chamber responsive to engine operating conditions to apply a secondary pressure on said wall to produce a further adjustment of said clearance in accordance with engine operating conditions, said last mentioned means being located within said first pressurizable chamber and including a wall to define the secondary pressurizable chamber, means on said wall movable upon pressurization of said secondary pressurizable chamber to produce a concentrated load on the deflectable wall to shape it in an axial direction to variably control blade tip clearance between the leading and trailing edges of said blades.
Claim 6
Dependent Claim
190 words
A turbine blade tip seal assembly for use in controlling blade tip gas bypass as motive fluid is directed across a turbine blade row comprising: a fixed outer shroud with a deflectable wall turbine rotor having blades thereon with tips located in close spaced relationship to said deflectable wall and including leading and trailing edges, means forming a first pressurizable chamber inflatable to a predetermined pressure to deflect said wall radially inwardly into a controlled radial clearance with said tips to prevent excessive gas bypass between said wall and said blade tips and means including a secondary pressurizable chamber responsive to engine operating conditions to apply a secondary pressure on said wall to produce a further adjustment of said clearance in accordance with engine operating conditions, said last mentioned means being located within said first pressurizable chamber and including a wall to define the secondary pressurizable chamber, means on said wall movable upon pressurization of said secondary pressurizable chamber to produce a concentrated load on the deflectable wall to shape it in an axial direction to variably control blade tip clearance between the leading and trailing edges of said blades.
Claim 7
Dependent Claim
205 words
A turbine blade tip seal assembly for use in controlling blade tip gas bypass as motive fluid is directed across a turbine blade row comprising: a fixed outer shroud with a deflectable wall, a turbine rotor having blades thereon with tips located in close spaced relationship to said deflectable wall and including leading and trailing edges, means forming a first pressurizable chamber inflatable to a predetermined pressure to deflect said wall radially inwardly into a controlled radial clearance with said tips to prevent excessive gas bypass between said wall and said blade tips, and means including a secondary pressurizable chamber responsive to engine operating conditions to apply to secondary pressure on said wall to produce a further adjustment of said clearance in accordance with engine operating conditions, said last mentioned means being located within said first pressurizable chamber and including a channel member having spaced walls to define a sealed secondary pressurizable chamber, said channel member further including a dependent rib forced against said deflectable wall by pressurization of said secondary pressurizable chamber thereby to produce a concentrated load on the deflectable wall to shape it in an axial direction to variably control blade tip clearance between the leading and trailing edges of said blades.
Claim 8
Dependent Claim
205 words
A turbine blade tip seal assembly for use in controlling blade tip gas bypass as motive fluid is directed across a turbine blade row comprising: a fixed outer shroud with a deflectable wall, a turbine rotor having blades thereon with tips located in close spaced relationship to said deflectable wall and including leading and trailing edges, means forming a first pressurizable chamber inflatable to a predetermined pressure to deflect said wall radially inwardly into a controlled radial clearance with said tips to prevent excessive gas bypass between said wall and said blade tips, and means including a secondary pressurizable chamber responsive to engine operating conditions to apply to secondary pressure on said wall to produce a further adjustment of said clearance in accordance with engine operating conditions, said last mentioned means being located within said first pressurizable chamber and including a channel member having spaced walls to define a sealed secondary pressurizable chamber, said channel member further including a dependent rib forced against said deflectable wall by pressurization of said secondary pressurizable chamber thereby to produce a concentrated load on the deflectable wall to shape it in an axial direction to variably control blade tip clearance between the leading and trailing edges of said blades.
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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) | 1984-01-27 | 1984-07-28 | 1985-01-27 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1988-01-27 | 1988-07-28 | 1989-01-27 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1992-01-27 | 1992-07-28 | 1993-01-27 | $7700.00 | Window Closed / Lapsed |