Patent DE611484C successfully refreshed from Google Patents.
US4154256A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Self stabilizing sonic inlet
Assignee: National Aeronautics and Space Administration
•
Filing: 1978-03-29
•
Granted: 1979-05-15
•
Expires: 1998-03-29
Abstract
Abstract There is disclosed an air inlet for a turbine engine suitable for use on a short takeoff and landing (STOL), a vertical takeoff and landing (VTOL) or a conventional takeoff and landing (CTOL) type of aircraft. A critical region in which critical flow occurs under certain conditions communicates with a less critical region of lower static pressure. Air is drawn away from the critical region and reinjected into the air flow at the less critical region. In one embodiment a circumferentially extended slot is provided in the inner surface of the air inlet at the windward side and downstream of the throat region. The slot communicates with a circumferential plenum chamber formed in the front of the air inlet just behind the lip. Circumferentially extending rows of apertures are provided on the lip establishing two sets of apertures spaced circumferentially away from the slot in opposite directions. The slot removes the boundary layer from the critical portion of the diffuser to minimize or eliminate flow pressure loss or separations resulting from diffusion or turning. The apertures are in a region of low static pressure on the lip of the inlet and serve as a source of suction to cause air flow into the slot.
Inventors
- 👤 Brent A. Miller
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 17:10
CPC Classifications
B; B64; B64D; B64D33/00; B64D33/02; B64D2033/0266; B64D2033/0286; Y; Y10; Y10T; Y10T137/00; Y10T137/0536
Claims Analysis
Total Claims: 23
Claim 1
Independent Claim
127 words
An air inlet for an aircraft turbine engine, said inlet being an annular body having inner and outer annular surfaces with an annular lip at its foreward end and a throat downstream of said lip, the minimum diameter of said throat lying on a plane perpendicular to the axis of said inlet diffuser, the improvement comprising: a circumferential plenum chamber formed in said diffuser around said throat; a primary aperture formed in said inner annular surface downstream of the plane of said throat at the windward side of said inlet in communication with said plenum chamber; and at least one secondary aperture in said inner annular surface upstream of the plane of said throat in communication with said plenum chamber and displaced circumferentially from said primary aperture.
Claim 2
Dependent Claim
127 words
An air inlet for an aircraft turbine engine, said inlet being an annular body having inner and outer annular surfaces with an annular lip at its foreward end and a throat downstream of said lip, the minimum diameter of said throat lying on a plane perpendicular to the axis of said inlet diffuser, the improvement comprising: a circumferential plenum chamber formed in said diffuser around said throat; a primary aperture formed in said inner annular surface downstream of the plane of said throat at the windward side of said inlet in communication with said plenum chamber; and at least one secondary aperture in said inner annular surface upstream of the plane of said throat in communication with said plenum chamber and displaced circumferentially from said primary aperture.
Claim 3
Dependent Claim
44 words
The inlet of claim 1 and having another secondary aperture in said inner annular wall upstream of the plane of said throat in communciation with said plenum chamber and displaced circumferentially from said slot in a direction opposite from said at least one aperture.
Claim 4
Dependent Claim
24 words
The inlet of claim 1 wherein said at least one secondary aperture and said another aperture each comprise a circumferentially extending row of apertures.
Claim 5
Dependent Claim
22 words
The inlet of claim 3 and including a second row of circumferentially extending apertures aft of each circumferentially extending row of apertures.
Claim 6
Dependent Claim
23 words
The inlet of claim 4 wherein the apertures of said second rows are staggered in relation to those of said circumferentially extending rows.
Claim 7
Dependent Claim
14 words
The inlet of claim 4 wherein said primary aperture is a circumferentially extending slot.
Claim 8
Dependent Claim
32 words
The inlet of claim 6 wherein said slot has a foreward wall and an aft wall, said walls being sloped in a forward direction with respect to the plane of said throat.
Claim 9
Dependent Claim
33 words
The inlet of claim 1 wherein said primary aperture has a forward wall and an aft wall, said walls being sloped in a forward direction with respect to the plane of said throat.
Claim 10
Dependent Claim
26 words
The inlet of claim 8 wherein said walls of said primary aperture make an angle of between 30° and 45° with the plane of said throat.
Claim 11
Dependent Claim
14 words
The inlet of claim 1 wherein said primary aperture is a circumferentially extending slot.
Claim 12
Dependent Claim
17 words
The inlet of claim 1 wherein said at least one secondary aperture is a circumferentially extending slot.
Claim 13
Dependent Claim
32 words
The inlet of claim 2 wherein said at least one secondary aperture is circular and wherein an axis perpendicular to the aperture slopes rearward with respect to the plane of said throat.
Claim 14
Dependent Claim
43 words
The inlet of claim 12 wherein said at least one aperture and said another secondary aperture each comprise first and second circumferentially extending parallel rows of apertures wherein axis perpendicular to the apertures slope rearwardly with respect to the plane of said throat.
Claim 15
Dependent Claim
25 words
The inlet of claim 13 wherein the axis of said apertures make an angle of between 30° and 45° with the plane of said throat.
Claim 16
Dependent Claim
21 words
The inlet of claim 14 wherein the apertures of said first and second rows are staggered with respect to each other.
Claim 17
Dependent Claim
109 words
An air inlet for a turbine engine of a subsonic aircraft wherein boundary layer flow separation occurs at a critical region in the inlet under certain conditions of forward velocity and angle of attack, the improvement comprising: primary aperture means at said critical region in said inlet; secondary aperture means at a region of substantially lower static pressure than said critical region; and conduit means connecting said primary and secondary apertures whereby boundary layer flow is drawn from said primary aperture and reinjected into air flowing into said inlet at a less critical region during conditions in which boundary layer flow separation would otherwise occur in said critical region.
Claim 18
Dependent Claim
109 words
An air inlet for a turbine engine of a subsonic aircraft wherein boundary layer flow separation occurs at a critical region in the inlet under certain conditions of forward velocity and angle of attack, the improvement comprising: primary aperture means at said critical region in said inlet; secondary aperture means at a region of substantially lower static pressure than said critical region; and conduit means connecting said primary and secondary apertures whereby boundary layer flow is drawn from said primary aperture and reinjected into air flowing into said inlet at a less critical region during conditions in which boundary layer flow separation would otherwise occur in said critical region.
Claim 19
Dependent Claim
26 words
The air inlet of claim 16 wherein said primary aperture means is a slot generally perpendicular to the direction of air flow at said critical region.
Claim 20
Dependent Claim
16 words
The air inlet of claim 16 wherein said secondary aperture means comprises a plurality of apertures.
Claim 21
Dependent Claim
30 words
The air inlet of claim 18 wherein said plurality of apertures comprise at least one row disposed generally perpendicular to the direction of air flow at said less critical region.
Claim 22
Dependent Claim
46 words
The air inlet of claim 19 wherein said plurality of apertures comprises at least two parallel rows generally perpendicular to the direction of air flow at said less critical region, the apertures of each row being staggered with respect to the apertures of an adjacent row.
Claim 23
Dependent Claim
29 words
The air inlet of claim 16 and including a throat, said primary aperture means being downstream of said throat and said secondary aperture means being upstream of said throat.
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) | 1982-05-14 | 1982-11-13 | 1983-05-15 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1986-05-14 | 1986-11-13 | 1987-05-15 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1990-05-14 | 1990-11-13 | 1991-05-15 | $7700.00 | Window Closed / Lapsed |