Patent US4131387A successfully refreshed from Google Patents.
US4131387A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Curved blade turbomachinery noise reduction
Assignee: General Electric Co
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Filing: 1976-02-27
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Granted: 1978-12-26
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Expires: 1996-02-27
Abstract
Abstract A turbomachinery stage comprising two axially spaced blade rows, one of which is rotatable, wherein the blades of the upstream row are contoured to present a leaned wake to the downstream row. In the preferred embodiment, the blades of the upstream row extend radially from a central hub and, at a radius above the hub, are physically curved circumferentially from a radial line through the hub. The physical lean locally complements the inherent aerodynamic lean at each radius such that the integrated acoustic power of the stage is essentially at a minimum, thus maximizing the acoustic attenuation. Preferably, the constraint is imposed that the blade physical curvature is essentially smooth, continuous and without an inflection point.
Inventors
- 👤 Stephen B. Kazin
- 👤 Ram K. Matta
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 21:31
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/12; F01D5/14; F01D5/141; F01D5/142; F05; F05D; F05D2250/00; F05D2250/70; F05D2250/71; F05D2250/713; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
137 words
In an aircraft gas turbine engine turbomachinery stage comprising adjacent upstream and downstream blade rows, one of which is rotatable, the improvement wherein the blades of the upstream row are physically curved with a local physical radial lean distribution in the circumferential direction such that the sum of the physical lean and the inherent aerodynamic lean in the circumferential direction results in the integrated acoustic power, P w , of the bladed stage being essentially at a minimum at the flight approach power operating condition where P w is generally defined by the relationship: ##EQU5## r hub = upstream blade row hub radius; r tip = upstream blade row tip radius; P m = RMS acoustic pressure; ρ = motive fluid density; c = acoustic velocity (speed of sound); r = radius; and dr = incremental radius.
Claim 2
Dependent Claim
137 words
In an aircraft gas turbine engine turbomachinery stage comprising adjacent upstream and downstream blade rows, one of which is rotatable, the improvement wherein the blades of the upstream row are physically curved with a local physical radial lean distribution in the circumferential direction such that the sum of the physical lean and the inherent aerodynamic lean in the circumferential direction results in the integrated acoustic power, P w , of the bladed stage being essentially at a minimum at the flight approach power operating condition where P w is generally defined by the relationship: ##EQU5## r hub = upstream blade row hub radius; r tip = upstream blade row tip radius; P m = RMS acoustic pressure; ρ = motive fluid density; c = acoustic velocity (speed of sound); r = radius; and dr = incremental radius.
Claim 3
Dependent Claim
162 words
In an aircraft gas turbine engine turbomachinery stage comprising axially spaced upstream and downstream blade rows, one of which is rotatable, the improvement wherein the blades of the upstream blade row extend generally radially relative to a central hub and, at radii above the hub, are physically curved and possessed of a local physical lean distribution such that the sum of the physical lean and the blade inherent aerodynamic lean in the circumferential direction results in the relationship of acoustic attenuation as a function of lean being essentially at one of its maximum values by minimizing the integrated acoustic power, P W , at the flight approach power operating condition where P w is generally defined by the relationship: ##EQU6## r hub = upstream blade row hub radius; r tip = upstream blade row tip radius; r = radius P m = RMS acoustic pressure; ρ = motive fluid density; c = acoustic velocity (speed of sound); and dr = incremental radius.
Claim 4
Dependent Claim
162 words
In an aircraft gas turbine engine turbomachinery stage comprising axially spaced upstream and downstream blade rows, one of which is rotatable, the improvement wherein the blades of the upstream blade row extend generally radially relative to a central hub and, at radii above the hub, are physically curved and possessed of a local physical lean distribution such that the sum of the physical lean and the blade inherent aerodynamic lean in the circumferential direction results in the relationship of acoustic attenuation as a function of lean being essentially at one of its maximum values by minimizing the integrated acoustic power, P W , at the flight approach power operating condition where P w is generally defined by the relationship: ##EQU6## r hub = upstream blade row hub radius; r tip = upstream blade row tip radius; r = radius P m = RMS acoustic pressure; ρ = motive fluid density; c = acoustic velocity (speed of sound); and dr = incremental radius.
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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) | 1981-12-25 | 1982-06-26 | 1982-12-26 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1985-12-25 | 1986-06-26 | 1986-12-26 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1989-12-25 | 1990-06-26 | 1990-12-26 | $7700.00 | Window Closed / Lapsed |