VAPOR CYCLE PROPULSION SYSTEM

• US 3,646,760 A
• Filed: 06/01/1970
• Issued: 03/07/1972
• Est. Priority Date: 06/01/1970
• Status: Expired due to Term

• Current Assignee: Rohr Industries, Inc. (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Jack P. Waidelich
• Inventors: Waidelich, Jack P.
• Primary Examiner(s): Hart, Douglas
• Application Number:
  US05/041,925
• Time in Patent Office: 645 Days
• Field of Search: 60/203,262,266,267,36,204
• US Class Current: 60/204
• CPC Class Codes: F02C 1/007 combination of cycles
• CPC Class Codes: F02C 7/224 Heating fuel before feeding to the burner
• CPC Class Codes: F02K 3/00 Plants including a gas turbine driving a compressor or a ducted fan

Abstract

System comprises duct with entire power plant within a duct. Axial flow compressor driven by vapor turbine produces entire thrust in form of airflow. Combustor combines minor portion of airflow with fuel and burns mixture to produce heat for vaporizing suitable working fluid. Latter may be water, mercury, or one of the alkali metals. Vaporized fluid goes to turbine and operates it to drive compressor. Exhaust from turbine goes to condenser located in airflow so that all rejected heat is added to airflow within duct to increase its energy. The vaporizer and turbine may be located within a center body to conserve heat for shaft horsepower. Combustion gases mix with air within duct so there is no primary combustion gas jet. High velocity of airflow is still much lower than turbojet, producing considerable noise reduction. Lower temperature of air further reduces noise and makes possible maximum use of acoustic surfaces inside duct. All heat rejected or lost goes into airflow to produce maximum efficiency. High cycle efficiency results in low hydrocarbon exhaust emission.

Claims

1. A jet propulsion system comprising:

a longitudinally extensive primary duct having a forward air inlet and an aft air outlet, and airflow-producing means located entirely within said duct;

said means including axial flow compressor means and vapor turbine means for driving the compressor means;

vaporizable working fluid means for operation of the turbine means;

heating means for vaporizing the working fluid means; and

condenser means flow-connected to the turbine means and located in the airflow through the primary duct and serving to liquefy vapor exhausted from the turbine means and transfer the heat of condensation to the airflow to increase its energy content;

said heating means including a heat exchanger for vaporizing at least some of the working fluid means;

the heat exchanger being located entirely within the primary duct and being segregated from the airflow through the primary duct;

a secondary duct to segregate a portion of the airflow produced by the compressor means;

combustion means in the secondary duct to combine the airflow therein with fuel to supply heat to the heat exchanger; and

means to discharge the products of combustion to the airflow within the primary duct upstream of its outlet to add its remaining heat energy to the air prior to discharge of the air from the primary duct outlet.

2. A system as claimed in claim 1;

said condenser means being located downstream of the compressor means to add its heat energy to the air after it has passed through the compressor means.

3. A system as claimed in claim 2;

said condenser means having acoustically treated surfaces to absorb a portion of the noise generated by the compressor means.

4. A system as claimed in claim 2;

and second condenser means located within said duct upstream of the compressor means and adapted to be flow-connected to the exhaust from the turbine means to provide additional cooling during high-power and high-temperature conditions.

5. A system as claimed in claim 4;

said second condenser means also having acoustically treated surfaces to absorb a portion of the noise generated by the compressor means and emitted in an axially forward direction.

6. A system as claimed in claim 1;

and portions of the walls of the flow-producing means and of the inner wall of the duct being provided with acoustic surfaces to absorb some of the noise generated by the airflow-producing means.

7. A system as claimed in claim 1;

said vaporizable working fluid means consisting of a single fluid;

said vapor turbine means consisting of a single vapor turbine compatible with said single fluid; and

said heat exchanger for vaporizing said single fluid consisting of a single heat exchanger compatible with said single fluid.

8. A system as claimed in claim 7;

said vaporizable working fluid means consisting of water.

9. A system as claimed in claim 7;

said vaporizable working fluid means consisting of mercury.

10. A system as claimed in claim 7;

said vapoRizable working fluid means consisting of one of the alkali metals.

11. A jet propulsion system comprising:

a longitudinally extensive duct having a forward air inlet and an aft air outlet;

an elongate center body having a central longitudinal axis substantially centered on the longitudinal axis of the duct and located entirely within the duct;

an axial flow compressor located within the duct to produce airflow from the inlet to the outlet thereof;

power supply means for driving the compressor;

said power supply means being located within the center body;

said power supply means including a combustor to supply heated products of combustion;

a heat exchanger to receive the products of combustion;

conduit means connected to said heat exchanger for flow of vaporizable working fluid to the heat exchanger and flow of vaporized working fluid therefrom;

vapor turbine means connected in driving relation to said compressor;

said conduit means being also connected to said turbine means to deliver vaporized working fluid thereto;

means to discharge the products of combustion from said heat exchanger into the airflow within the duct; and

condenser means located in the airflow through the duct and serving to liquefy vapor exhausted from the turbine means and transfer the heat of condensation to the airflow to increase its energy content.

12. A system as claimed in claim 11;

said condenser means extending at least partially across said duct and being located downstream of the compressor to add its heat energy to he air after it has passed through the compressor.

13. A system as claimed in claim 12;

and second condenser means extending at least partially across said duct upstream of the compressor and adapted to be flow-connected to the exhaust from the turbine means to provide additional cooling during high-power and high-temperature conditions.

14. A system as claimed in claim 11;

and acoustic surfaces on portions of the outer wall of the center body and the inner wall of the duct to absorb sound generated by the compressor.

15. A method of producing propulsive jet thrust with maximum efficiency, minimum pollutant emission, and minimum noise emission, comprising:

producing a high-velocity primary axial flow of air;

passing said flow through a confined zone having an inlet and an outlet;

segregating a minor portion of the air from said primary flow;

combining said minor portion of said air with fuel and combusting the mixture separate from said primary flow;

applying the heat of combustion to a vaporizable working fluid power system within said zone;

utilizing said power system within said zone to produce said primary flow of air; and

transferring all of the waste heat emitted by said power system to the air within said zone prior to its discharge from said outlet.