US5368440A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Radial turbo machine
Assignee: Concepts ETI Inc
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Filing: 1993-03-11
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Granted: 1994-11-29
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Expires: 2013-03-11
Abstract
Abstract A radial turbo machine has an impeller and a diffuser with a plurality of airfoil vanes. The airfoil vanes have a design point angle of attack substantially equal to or less than the angle of attack corresponding to the classic onset of pressure side stall of the airfoil vane. The pressure side of the airfoil vane faces away from the rotational axis of the impeller while the suction side faces towards the impeller's rotational axis.
Inventors
- 👤 David Japikse
- 👤 David M. Karon
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 07:09
CPC Classifications
F; F04; F04D; F04D29/00; F04D29/40; F04D29/42; F04D29/44; F04D29/441; F04D29/444; F05; F05D; F05D2250/00; F05D2250/50; F05D2250/52
Claims Analysis
Total Claims: 19
Claim 1
Independent Claim
83 words
A radial turbo machine comprising: an impeller means having a rotational axis; a diffuser means having a plurality of airfoil vanes, said airfoil vanes each having a pressure side facing away from and a suction side facing towards the rotational axis of said impeller means with at least some of said airfoil vanes having a design point angle of attack substantially equal to or less than an angle of attack corresponding to the classic onset of pressure side stall of the airfoil vane.
Claim 2
Dependent Claim
83 words
A radial turbo machine comprising: an impeller means having a rotational axis; a diffuser means having a plurality of airfoil vanes, said airfoil vanes each having a pressure side facing away from and a suction side facing towards the rotational axis of said impeller means with at least some of said airfoil vanes having a design point angle of attack substantially equal to or less than an angle of attack corresponding to the classic onset of pressure side stall of the airfoil vane.
Claim 3
Dependent Claim
17 words
The radial turbo machine of claim 1 wherein at least some of said airfoil vanes are cambered.
Claim 4
Dependent Claim
15 words
The radial turbo machine of claim 1 wherein all of said airfoil vanes are cambered.
Claim 5
Dependent Claim
17 words
The radial turbo machine of claim 1 wherein at least some of said airfoil vanes are uncambered.
Claim 6
Dependent Claim
15 words
The radial turbo machine of claim 1 wherein all of said airfoil vanes are uncambered.
Claim 7
Dependent Claim
39 words
The radial turbo machine of claim 1 wherein said airfoil vanes have an airfoil shape corresponding substantially to NACA 65-series blade sections with a lift coefficient from 0.0 to 1.2 inclusive and a thickness from 4% to 15% inclusive.
Claim 8
Dependent Claim
32 words
The radial turbo machine of claim 6 wherein said airfoil vanes have a NACA 65-04-06 blade section and said design point angle of attack is substantially equal to or less than +3.5°.
Claim 9
Dependent Claim
23 words
The radial turbo machine of claim 7 wherein the design point angle of attack is in the range from -3.5° to +3.5° inclusive.
Claim 10
Dependent Claim
18 words
The radial turbo machine of claim 7 wherein the design point angle of attack is substantially at 0°.
Claim 11
Dependent Claim
42 words
The radial turbo machine of claim 1 wherein all of said airfoil vanes have a design point angle of attack equal to or less than ab angle of attack corresponding to the classic onset of pressure side stall of the airfoil vane.
Claim 12
Dependent Claim
17 words
The radial turbo machine of claim 10 wherein at least some of said airfoil vanes are cambered.
Claim 13
Dependent Claim
15 words
The radial turbo machine of claim 11 wherein all of said airfoil vanes are cambered.
Claim 14
Dependent Claim
17 words
The radial turbo machine of claim 10 wherein at least some of said airfoil vanes are uncambered.
Claim 15
Dependent Claim
15 words
The radial turbo machine of claim 13 wherein all of said airfoil vanes are uncambered.
Claim 16
Dependent Claim
39 words
The radial turbo machine of claim 10 wherein said airfoil vanes have an airfoil shape corresponding substantially to NACA 65-series blade sections with a lift coefficient from 0.0 to 1.2 inclusive and a thickness from 4% to 15% inclusive.
Claim 17
Dependent Claim
32 words
The radial turbo machine of claim 15 wherein said airfoil vanes have a NACA 65-04-06 blade section and said design point angle of attack is substantially equal to or less than +3.5°.
Claim 18
Dependent Claim
23 words
The radial turbo machine of claim 16 wherein the design point angle of attack is in the range from -3.5° to +3.5° inclusive.
Claim 19
Dependent Claim
18 words
The radial turbo machine of claim 16 wherein the design point angle of attack is substantially at 0°.
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) | 1997-11-28 | 1998-05-30 | 1998-11-29 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2001-11-28 | 2002-05-30 | 2002-11-29 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2005-11-28 | 2006-05-30 | 2006-11-29 | $7700.00 | Window Closed / Lapsed |