US3765168A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Water recovery
Assignee: Motors Liquidation Co
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Filing: 1972-08-24
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Granted: 1973-10-16
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Expires: 1992-08-24
Abstract
Abstract A system and method for recovering clean water from the air flowing into and through a gas turbine engine. Low pressure air drawn from the engine compressor is fed to a receiver. Compressed air from a higher stage of the compressor is cooled by atmospheric air which may be previously spray-cooled. The compressed air is further cooled by heat exchange with exhaust air from the system, and then expanded to further cool the air and lower its pressure. The two flows of air are then mixed in a receiver about 0*C. to precipitate water from the mixed air flow. The water collected in the receiver is used for cooling the turbine of the engine and also, if desired, for spray cooling the atmospheric air referred to above. The air discharged from the receiver is used to cool the compressed air and then discharged to exhaust.
Inventors
- 👤 J Wagle
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 14:25
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/12; F02C7/16; Y; Y02; Y02T; Y02T50/00; Y02T50/60; Y10; Y10S; Y10S55/00; Y10S55/17
Claims Analysis
Total Claims: 14
Claim 1
Independent Claim
154 words
A method of cooling a gas turbine engine having a multistage compressor and a turbine comprising bleeding a first flow of air at slightly above atmospheric pressure from a low stage of the compressor, bleeding a second flow of air at substantially above atmospheric pressure from a higher stage of the compressor, cooling the second flow by heat exchange to a cooling medium, further cooling the second flow of air by heat exchange with a flow of cooled air, expanding the second flow of air into a receiver to cool the air and supply the receiver with cooled low pressure air, supplying the first flow of air into the receiver and mixing the two flows in the receiver to condense and collect water from the mixed air flows and provide the said flow of cooled air for cooling the said second flow, and supplying the collected water to the turbine to cool the turbine.
Claim 2
Independent Claim
154 words
A method of cooling a gas turbine engine having a multistage compressor and a turbine comprising bleeding a first flow of air at slightly above atmospheric pressure from a low stage of the compressor, bleeding a second flow of air at substantially above atmospheric pressure from a higher stage of the compressor, cooling the second flow by heat exchange to a cooling medium, further cooling the second flow of air by heat exchange with a flow of cooled air, expanding the second flow of air into a receiver to cool the air and supply the receiver with cooled low pressure air, supplying the first flow of air into the receiver and mixing the two flows in the receiver to condense and collect water from the mixed air flows and provide the said flow of cooled air for cooling the said second flow, and supplying the collected water to the turbine to cool the turbine.
Claim 3
Independent Claim
167 words
A method of cooling a gas turbine engine having a multistage compressor and a turbine comprising bleeding a first flow of air at slightly above atmospheric pressure from a low stage of the compressor, bleeding a second flow of air at Substantially above atmospheric pressure from a higher stage of the compressor, cooling the second flow of air to a temperature above atmospheric by heat exchange to atmosphere, further cooling the second flow of air by heat exchange with a flow of cooled air, expanding the second flow of air into a receiver to cool the air and supply the receiver with cooled low pressure air, supplying the first flow of air into the receiver and mixing the two flows in the receiver to cool the mixed flows to near 0*C. to condense and collect water from the mixed air flows and provide the said flow of cooled air for cooling the said second flow, and supplying the collected water to the turbine to cool the turbine.
Claim 4
Independent Claim
167 words
A method of cooling a gas turbine engine having a multistage compressor and a turbine comprising bleeding a first flow of air at slightly above atmospheric pressure from a low stage of the compressor, bleeding a second flow of air at Substantially above atmospheric pressure from a higher stage of the compressor, cooling the second flow of air to a temperature above atmospheric by heat exchange to atmosphere, further cooling the second flow of air by heat exchange with a flow of cooled air, expanding the second flow of air into a receiver to cool the air and supply the receiver with cooled low pressure air, supplying the first flow of air into the receiver and mixing the two flows in the receiver to cool the mixed flows to near 0*C. to condense and collect water from the mixed air flows and provide the said flow of cooled air for cooling the said second flow, and supplying the collected water to the turbine to cool the turbine.
Claim 5
Independent Claim
167 words
A method of cooling a gas turbine engine having a multistage compressor and a turbine comprising bleeding a first flow of air at slightly above atmospheric pressure from a low stage of the compressor, bleeding a second flow of air at Substantially above atmospheric pressure from a higher stage of the compressor, cooling the second flow of air to a temperature above atmospheric by heat exchange to atmosphere, further cooling the second flow of air by heat exchange with a flow of cooled air, expanding the second flow of air into a receiver to cool the air and supply the receiver with cooled low pressure air, supplying the first flow of air into the receiver and mixing the two flows in the receiver to cool the mixed flows to near 0*C. to condense and collect water from the mixed air flows and provide the said flow of cooled air for cooling the said second flow, and supplying the collected water to the turbine to cool the turbine.
Claim 6
Independent Claim
167 words
A method of cooling a gas turbine engine having a multistage compressor and a turbine comprising bleeding a first flow of air at slightly above atmospheric pressure from a low stage of the compressor, bleeding a second flow of air at Substantially above atmospheric pressure from a higher stage of the compressor, cooling the second flow of air to a temperature above atmospheric by heat exchange to atmosphere, further cooling the second flow of air by heat exchange with a flow of cooled air, expanding the second flow of air into a receiver to cool the air and supply the receiver with cooled low pressure air, supplying the first flow of air into the receiver and mixing the two flows in the receiver to cool the mixed flows to near 0*C. to condense and collect water from the mixed air flows and provide the said flow of cooled air for cooling the said second flow, and supplying the collected water to the turbine to cool the turbine.
Claim 7
Independent Claim
197 words
A method of cooling a gas turbine engine having a multistage compressor and a turbine comprising bleeding a first flow of air at slightly above atmospheric pressure from a low stage of the compressor, bleeding a second flow of air at substantially above atmospheric pressure from a higher stage of the compressor, providing a third flow of air at substantially atmospheric condition, cooling the third flow by evaporation of water, cooling the second flow of air by heat exchange with the cooled third flow, further cooling the second flow of air by heat exchange with a fourth flow of cooled air, expanding the second flow of air into a receiver to cool the air and supply the receiver with cooled low pressure air, supplying the first flow of air into the receiver and mixing the two flows in the receiver to cool the mixed flows to near 0*C. to condense and collect water from the mixed air flows and provide the said fourth flow of cooled air for cooling the said second flow, and supplying the collected water to the third flow of air for cooling the third flow and to the turbine to cool the turbine.
Claim 8
Independent Claim
197 words
A method of cooling a gas turbine engine having a multistage compressor and a turbine comprising bleeding a first flow of air at slightly above atmospheric pressure from a low stage of the compressor, bleeding a second flow of air at substantially above atmospheric pressure from a higher stage of the compressor, providing a third flow of air at substantially atmospheric condition, cooling the third flow by evaporation of water, cooling the second flow of air by heat exchange with the cooled third flow, further cooling the second flow of air by heat exchange with a fourth flow of cooled air, expanding the second flow of air into a receiver to cool the air and supply the receiver with cooled low pressure air, supplying the first flow of air into the receiver and mixing the two flows in the receiver to cool the mixed flows to near 0*C. to condense and collect water from the mixed air flows and provide the said fourth flow of cooled air for cooling the said second flow, and supplying the collected water to the third flow of air for cooling the third flow and to the turbine to cool the turbine.
Claim 9
Independent Claim
167 words
A system for cooling a gas turbine engine having a multistage compressor and a turbine, the system comprising, in combination, means for bleeding a first flow of air at slightly above atmospheric pressure from a low stage of the compressor, means for bleeding a second flow of air at substantially above atmospheric pressure from a higher stage of the compressor, first heat exchange means for cooling the second flow of air by heat exchange to the atmosphere, second heat exchange means for further cooling the second flow of air by heat exchange with a flow of cooled air, means for expanding and thus still further cooling the second flow of air, means for mixing the still further cooled flow with the first flow to condense and discharge atmospheric water from the mixed air flows, means for conducting the mixed air flows through the second heat exchange means, means to collect the discharged water, and means for supplying the collected water to the turbine to cool the turbine.
Claim 10
Independent Claim
167 words
A system for cooling a gas turbine engine having a multistage compressor and a turbine, the system comprising, in combination, means for bleeding a first flow of air at slightly above atmospheric pressure from a low stage of the compressor, means for bleeding a second flow of air at substantially above atmospheric pressure from a higher stage of the compressor, first heat exchange means for cooling the second flow of air by heat exchange to the atmosphere, second heat exchange means for further cooling the second flow of air by heat exchange with a flow of cooled air, means for expanding and thus still further cooling the second flow of air, means for mixing the still further cooled flow with the first flow to condense and discharge atmospheric water from the mixed air flows, means for conducting the mixed air flows through the second heat exchange means, means to collect the discharged water, and means for supplying the collected water to the turbine to cool the turbine.
Claim 11
Independent Claim
180 words
A system for cooling a gas turbine engine having a multistage compressor and a turbine, the system comprising, in combination, means for bleeding a first flow of air at slightly above atmospheric pressure from a low stage of the compressor, means for bleeding a second flow of air at substantially above atmospheric pressure from a higher stage of the compressor, first heat exchange means for cooling the second flow of air by heat exchange to the atmosphere to a temperature above atmospheric, second heat exchange means for further cooling the second flow of air by heat exchange with a flow of cooled air, means for expanding and thus still further cooling the second flow of air, means for mixing the still further cooled flow with the first flow to cool the mixed flows to near 0*C. to condense and discharge atmospheric water from the mixed air flows, means for conducting the mixed air flows through the second heat exchange means, means to collect the discharged water, and means for supplying the collected water to the turbine to cool the turbine.
Claim 12
Independent Claim
180 words
A system for cooling a gas turbine engine having a multistage compressor and a turbine, the system comprising, in combination, means for bleeding a first flow of air at slightly above atmospheric pressure from a low stage of the compressor, means for bleeding a second flow of air at substantially above atmospheric pressure from a higher stage of the compressor, first heat exchange means for cooling the second flow of air by heat exchange to the atmosphere to a temperature above atmospheric, second heat exchange means for further cooling the second flow of air by heat exchange with a flow of cooled air, means for expanding and thus still further cooling the second flow of air, means for mixing the still further cooled flow with the first flow to cool the mixed flows to near 0*C. to condense and discharge atmospheric water from the mixed air flows, means for conducting the mixed air flows through the second heat exchange means, means to collect the discharged water, and means for supplying the collected water to the turbine to cool the turbine.
Claim 13
Independent Claim
216 words
A system for cooling a gas turbine engine having a multistage compressor and a turbine, the system comprising, in combination, meanS for bleeding a first flow of air at slightly above atmospheric pressure from a low stage of the compressor, means for bleeding a second flow of air at substantially above atmospheric pressure from a higher stage of the compressor, means for providing a third flow of air at substantially atmospheric condition, means for cooling the third flow by evaporation of water, first heat exchange means for cooling the second flow of air by heat exchange with the cooled third flow, second heat exchange means for further cooling the second flow of air by heat exchange with a fourth flow of cooled air, means for expanding and thus still further cooling the second flow of air, means for mixing the still further cooled flow with the first flow to cool the mixed flows to near 0*C. to condense and discharge atmospheric water from the mixed air flows and provide the fourth air flow, means for conducting the fourth air flow through the second heat exchange means, means to collect the discharged water, and means for supplying the collected water to the means for cooling the third air flow and to the turbine to cool the turbine.
Claim 14
Independent Claim
216 words
A system for cooling a gas turbine engine having a multistage compressor and a turbine, the system comprising, in combination, meanS for bleeding a first flow of air at slightly above atmospheric pressure from a low stage of the compressor, means for bleeding a second flow of air at substantially above atmospheric pressure from a higher stage of the compressor, means for providing a third flow of air at substantially atmospheric condition, means for cooling the third flow by evaporation of water, first heat exchange means for cooling the second flow of air by heat exchange with the cooled third flow, second heat exchange means for further cooling the second flow of air by heat exchange with a fourth flow of cooled air, means for expanding and thus still further cooling the second flow of air, means for mixing the still further cooled flow with the first flow to cool the mixed flows to near 0*C. to condense and discharge atmospheric water from the mixed air flows and provide the fourth air flow, means for conducting the fourth air flow through the second heat exchange means, means to collect the discharged water, and means for supplying the collected water to the means for cooling the third air flow and to the turbine to cool the turbine.
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) | 1976-10-15 | 1977-04-16 | 1977-10-16 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-10-15 | 1981-04-16 | 1981-10-16 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-10-15 | 1985-04-16 | 1985-10-16 | $7700.00 | Window Closed / Lapsed |