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Patent US5779196A successfully refreshed from Google Patents.
US5779196A
Expired / Lapsed
US
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Ram air drive laminar flow control system
Assignee: Boeing Co
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Filing: 1995-12-08
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Granted: 1998-07-14
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Expires: 2015-12-08
Abstract
Abstract An improvement to supersonic laminar flow control suction systems, including an inlet air duct (32) for providing subsonic ram engine inlet air, is provided. The inlet air duct (32) supplies air pressure power to one or more turbines of suction system compressor units alone for flight conditions at or above a particular minimum speed and minimum altitude, and in conjunction with engine compressor bleed air for flight conditions below the minimum speed and minimum altitude. The inlet air duct (32) is angled in the direction of subsonic airflow approximately 30 degrees from the horizontal off an opening in an upper wall of a subsonic diffuser of an engine inlet on a supersonic aircraft, and is connected to a power input line that feeds one or more compressor unit turbines. A check valve prevents backflow of air toward the engine inlet. The suction system further includes a short compressor output duct (38) and a short turbine output duct (40). These two ducts join to form a single exhaust passage (42), ensuring a moderate overall suction air exhaust gas temperature.
Inventors
- 👤 Thomas Timar
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 10:16
CPC Classifications
B; B64; B64C; B64C21/00; B64C21/02; B64C21/06; B64C2230/00; B64C2230/04; B64C2230/06; B64C2230/22; Y; Y02; Y02T; Y02T50/00; Y02T50/10
Claims Analysis
Total Claims: 20
Claim 1
Independent Claim
140 words
In a boundary layer flow control suction system for an aircraft including a supersonic engine inlet having a region of subsonic airflow, a source of engine bleed air, and a boundary layer suction compressor unit having a turbine driving a compressor, the compressor being connected to a suction surface of the aircraft for suctioning external air from an aircraft surface; the improvement comprising a turbine input line connected to both the region of subsonic airflow and the source of engine bleed air during flight at less than a predetermined minimum aircraft speed M min and minimum aircraft altitude A min , and connected only to the region of subsonic airflow during flight at at least the M min and A min ; whereby the turbine is powered from air flowing through the turbine input line during boundary layer flow control.
Claim 2
Dependent Claim
140 words
In a boundary layer flow control suction system for an aircraft including a supersonic engine inlet having a region of subsonic airflow, a source of engine bleed air, and a boundary layer suction compressor unit having a turbine driving a compressor, the compressor being connected to a suction surface of the aircraft for suctioning external air from an aircraft surface; the improvement comprising a turbine input line connected to both the region of subsonic airflow and the source of engine bleed air during flight at less than a predetermined minimum aircraft speed M min and minimum aircraft altitude A min , and connected only to the region of subsonic airflow during flight at at least the M min and A min ; whereby the turbine is powered from air flowing through the turbine input line during boundary layer flow control.
Claim 3
Dependent Claim
21 words
The improvement according to claim 1, wherein the suction system is a laminar flow control suction system for a supersonic aircraft.
Claim 4
Dependent Claim
34 words
The improvement according to claim 1, wherein the subsonic region is a subsonic diffuser and the airflow is diverted from the subsonic region at a location along an upper surface of the subsonic diffuser.
Claim 5
Dependent Claim
30 words
The improvement according to claim 1, wherein the subsonic region includes sidewall surfaces and the inlet airflow is diverted from the sidewall surfaces at an angle of approximately 30 degrees.
Claim 6
Dependent Claim
44 words
The improvement according to claim 1, wherein the suction system includes an exhaust passage connecting to an output of the compressor, the exhaust passage for exhausting pressurized suction air, the improvement further comprising a turbine output duct connecting the turbine to the exhaust passage.
Claim 7
Dependent Claim
146 words
A laminar flow control system for a supersonic aircraft comprising: (a) a suction region located on an aerodynamic surface of the aircraft, the suction region including a plurality of perforations through which suction air is drawn into the aircraft; (b) a supersonic engine inlet including a region of subsonic airflow; (c) a source of engine bleed air; and (d) a compressor unit for drawing in the suction air from the suction region, the compressor unit including a turbine driving a compressor; the turbine being connected to and powered by air from both the subsonic airflow region and the engine bleed air during flight at less than a predetermined minimum aircraft speed M min and minimum aircraft altitude A min ; and being connected and powered by air from only the region of subsonic airflow during flight at and above the M min and A min .
Claim 8
Dependent Claim
146 words
A laminar flow control system for a supersonic aircraft comprising: (a) a suction region located on an aerodynamic surface of the aircraft, the suction region including a plurality of perforations through which suction air is drawn into the aircraft; (b) a supersonic engine inlet including a region of subsonic airflow; (c) a source of engine bleed air; and (d) a compressor unit for drawing in the suction air from the suction region, the compressor unit including a turbine driving a compressor; the turbine being connected to and powered by air from both the subsonic airflow region and the engine bleed air during flight at less than a predetermined minimum aircraft speed M min and minimum aircraft altitude A min ; and being connected and powered by air from only the region of subsonic airflow during flight at and above the M min and A min .
Claim 9
Dependent Claim
51 words
The laminar flow control system according to claim 6, wherein the suction system is a laminar flow control suction system for a supersonic aircraft; the subsonic region is a subsonic diffuser; and the airflow is diverted from the subsonic region at a location along an upper surface of the subsonic diffuser.
Claim 10
Dependent Claim
33 words
The laminar flow control system according to claim 7, wherein the subsonic region includes sidewall surfaces and the inlet airflow is diverted from the sidewall surfaces at an angle of approximately 30 degrees.
Claim 11
Dependent Claim
127 words
In a method of boundary layer flow control suction for an aerospace vehicle including a supersonic engine inlet having a region of subsonic airflow and including a source of engine bleed air, the method including suctioning air from an aerodynamic surface of the aerospace vehicle using a compressor driven by a turbine, the compressor being connected to the aerodynamic surface; the improvement comprising powering the turbine using pressurized air from both the subsonic airflow region and the engine bleed air source during flight at less than a predetermined minimum aerospace vehicle speed M min and minimum aerospace vehicle altitude A min , and powering the turbine using only pressurized air from the subsonic airflow region during flight at at least the M min and A min .
Claim 12
Dependent Claim
127 words
In a method of boundary layer flow control suction for an aerospace vehicle including a supersonic engine inlet having a region of subsonic airflow and including a source of engine bleed air, the method including suctioning air from an aerodynamic surface of the aerospace vehicle using a compressor driven by a turbine, the compressor being connected to the aerodynamic surface; the improvement comprising powering the turbine using pressurized air from both the subsonic airflow region and the engine bleed air source during flight at less than a predetermined minimum aerospace vehicle speed M min and minimum aerospace vehicle altitude A min , and powering the turbine using only pressurized air from the subsonic airflow region during flight at at least the M min and A min .
Claim 13
Dependent Claim
34 words
The improvement according to claim 9, wherein the compressor and the turbine produce exhaust air, the improvement further comprising combining the compressor and turbine exhaust airs and emitting the combination from the aerospace vehicle.
Claim 14
Dependent Claim
21 words
The improvement according to claim 9, wherein the subsonic airflow region is located along an upper surface of the engine inlet.
Claim 15
Dependent Claim
30 words
The improvement according to claim 9, wherein the subsonic region includes sidewall surfaces and the pressurized air is diverted from the sidewall surfaces at an angle of approximately 30 degrees.
Claim 16
Independent Claim
134 words
A method of using a suctioning system for suctioning air from an aerodynamic surface of a supersonic aircraft comprising: (a) providing a suction surface on the aerodynamic surface; (b) providing a supersonic engine inlet having a region of subsonic airflow, providing a source of engine bleed air, connecting a compressor to the suction surface, and driving the compressor with a turbine; (c) drawing air from the suction surface with the compressor by powering the turbine using pressurized air from both the subsonic airflow region and the engine bleed air source during flight at less than a predetermined minimum aircraft speed M min and minimum aircraft altitude A min , and powering the turbine using only pressurized air from the subsonic airflow region during flight at at least the M min and A min .
Claim 17
Independent Claim
134 words
A method of using a suctioning system for suctioning air from an aerodynamic surface of a supersonic aircraft comprising: (a) providing a suction surface on the aerodynamic surface; (b) providing a supersonic engine inlet having a region of subsonic airflow, providing a source of engine bleed air, connecting a compressor to the suction surface, and driving the compressor with a turbine; (c) drawing air from the suction surface with the compressor by powering the turbine using pressurized air from both the subsonic airflow region and the engine bleed air source during flight at less than a predetermined minimum aircraft speed M min and minimum aircraft altitude A min , and powering the turbine using only pressurized air from the subsonic airflow region during flight at at least the M min and A min .
Claim 18
Dependent Claim
42 words
The method of suctioning air according to claim 13, wherein the compressor and the turbine produce exhaust air, the improvement further comprising cooling the turbine exhaust air by combining the compressor and turbine exhaust airs and emitting the combination from the aircraft.
Claim 19
Dependent Claim
52 words
The method of suctioning air according to claim 13, wherein the suctioning system is a laminar flow control suction system for a supersonic aircraft; the subsonic region is a subsonic diffuser; and the pressurized air is diverted from the subsonic region at a location along an upper surface of the subsonic diffuser.
Claim 20
Dependent Claim
33 words
The method of suctioning air according to claim 13, wherein the subsonic region includes sidewall surfaces and the pressurized air is diverted from the sidewall surfaces at an angle of approximately 30 degrees.
References Cited (Backward Citations)
USRE23105E
Cited
US1691942A
Cited
US1829616A
Cited
US1993419A
Cited
US2041790A
Cited
US2223744A
Cited
US2416991A
Cited
US3058695A
Cited
US3801048A
Cited
US3981466A
Cited
US4477040A
Cited
US4463772A
Cited
GB2242235A
Cited
US5143329A
Cited
US5114103A
Cited
US5348256A
Cited
US5236155A
Cited
US5535967A
Cited
US5447283A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 2001-07-13 | 2002-01-12 | 2002-07-14 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2005-07-13 | 2006-01-12 | 2006-07-14 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2009-07-13 | 2010-01-12 | 2010-07-14 | $7700.00 | Window Closed / Lapsed |