Granted Patent B2

US 7,117,676 · App. 10/397,881 · Granted Oct 10, 2006

Abstract

Claims (114)

1. A combustion system for use in a gas powered turbine which combusts a fuel in the presence of an oxidizer comprising:

a first injector member to inject a first volume of fuel into a volume of said oxidizer;

a mixer to mix said volume of oxidizer with said first volume of fuel;

a heater to heat said volume of oxidizer to form a volume of high energy oxidizer;

a second injector member to inject a second volume of fuel into said volume of high energy oxidizer;

wherein substantially all the fuel provided through said second injector member reaches a temperature at substantially the same time;

wherein said heater comprises:

a fuel supply system to provide said first volume of said fuel to said volume of oxidizer:

a heat exchanger including:

a heater pathway extending along a first axis;

a cooling pathway extending along a second axis;

wherein said heater pathway is in thermal contact with said cooling pathway;

wherein the oxidizer is adapted to first flow through said cooling pathway and then through said heater pathway; and

wherein said volume of oxidizer is adapted to first flow past said heater pathway through said cooling pathway, thereby receiving thermal energy from said heater pathway.

2. The combustion system of claim 1 ,

wherein said heater pathway comprises a plurality of heater tubes, that form a plurality of heater tube columns, each of said heater tube columns is spaced apart transversally to said first axis and defining a plurality of channels adapted for allowing the oxidizer to flow therethrough;

wherein said cooling pathway comprises a plurality of cooling tubes that form a plurality of cooling tube columns, each of said cooling tube columns is spaced apart transversally to said second axis; and

wherein said cooling tubes extend substantially adjacent said heater tubes along said second axis for at least a portion of the length of said heater tubes.

3. A combustion system for use in a gas powered turbine which combusts a fuel in the presence of an oxidizer comprising:

a first injector member to inject a first volume of fuel into a volume of said oxidizer;

a mixer to mix said volume of oxidizer with said first volume of fuel;

a heater to add energy to said volume of oxidizer to form a volume of high energy oxidizer;

a second injector member to inject a second volume of fuel into said volume of high energy oxidizer;

wherein substantially all the fuel provided through said second injector member reaches a temperature at substantially the same time;

wherein said mixer comprises:

a plurality of conduits defining at least a portion of a coolant pathway, each conduit including at least one wall and an inlet defining an inlet area;

said wall defining at least one outlet aperture having an outlet aperture area;

wherein a fluid flows into said conduit through said inlet area and out through said outlet aperture; and

wherein a velocity head of said fluid exiting said outlet apertures is less than a velocity head of said fluid flowing through said conduit.

4. The combustion system of claim 3 , wherein:

said plurality of conduits are arranged into at least two columns defining a void therebetween;

said first injector injects said first volume of fuel into said void;

said volume of oxidizer exits said outlet apertures into said void to mix with said first volume of fuel; and

said outlet apertures reduce the velocity head of said oxidizer to assist in achieving a selected pressure of said oxidizer and said volume of fuel.

5. The combustion system of claim 3 , wherein

each of said plurality of conduits define a column and two respective columns define a void therebetween;

said first injector injects said first volume of fuel into said void;

said volume of oxidizer exits said outlet apertures into said void to mix with said first volume of fuel; and

said outlet apertures reduce the velocity head of said oxidizer to assist in achieving a selected pressure of said oxidizer and said volume of fuel.

6. A combustion system for use in a gas powered turbine which combusts a fuel in the presence of an oxidizer comprising:

a first injector member to inject a first volume of fuel into a volume of said oxidizer;

a mixer to mix said volume of oxidizer with said first volume of fuel;

a heater to add energy to said volume of oxidizer to form a volume of high energy oxidizer;

a second injector member to inject a second volume of fuel into said volume of high energy oxidizer; and

a combustion suppressor disposed in said mixer to substantially eliminate any combustion of said first volume of fuel before said first volume of fuel enters said heater;

wherein substantially all the fuel provided through said second injector member reaches a temperature at substantially the same time.

7. The combustion system of claim 6 , further comprising:

a mixing area, wherein said first volume of fuel and said volume of oxidizer are mixed in said mixing area before entering said heater; and

wherein said combustion suppressor includes a member disposed in said mixing area to reduce a distance of said mixing area to at least a quenching distance of said fuel.

8. The combustion system of claim 6 , further comprising:

at least two conduits spaced apart to define a mixing area;

a coating disposed on an exterior of said conduits;

wherein said first volume of fuel and said volume of oxidizer are mixed in said mixing area before entering said heater; and

wherein said coating substantially inhibits combustion of said fuel.

9. A gas powered turbine, comprising:

a compressor to produce compressed atmospheric air to provide an oxidizer for the gas powered turbine;

a combustion system for mixing and combusting a fuel injected into the compressed atmospheric air to produce an expanding gas;

a turbine fan which is powered by the expanding gases:

said combustion system includes:

a pre-heat area; and

a pre-mix area for mixing the fuel with the compressed air before the air enters the pre-heat area; and

wherein said compressed air maintains a generally constant pressure from said compressor to said pre-heat area.

10. The gas powered turbine of claim 9 , further comprising:

a first fuel line to supply a first portion of fuel to the compressed atmospheric air which is used in the pre-heat area to heat the compressed atmospheric air to a hypergolic temperature so as to produce a volume of hypergolic air;

a second fuel line to supply a second portion of said volume of fuel to hypergolic air;

a first injector system to provide said second portion of fuel to said volume of hypergolic air before any substantial portion of said second portion of fuel combusts; and

wherein substantially all of said second portion of fuel combusts at substantially the same time such that the gas powered turbine emits substantially only selected chemical compounds.

11. The combustion system of claim 9 , wherein said pre-mix area includes:

a plurality of conduits defining at least a portion of a coolant pathway, each conduit including at least one wall and an inlet defining an inlet area;

said wall defining at least one outlet aperture having an outlet aperture area;

wherein said compressed air flows into said conduit through said inlet area and out through said outlet aperture; and

wherein a velocity head of said compressed air exiting said outlet apertures is less than a velocity head of said compressed air flowing through said conduit.

12. The combustion system of claim 11 , further comprising:

a second injector system;

wherein said plurality of conduits are arranged into at least two columns defining a void therebetween;

said second injector system injects said first volume of fuel into said void;

said volume of compressed air exits said outlet apertures into said void to mix with said volume of fuel; and

said outlet apertures reduce a velocity head of said compressed air to assist in maintaining a selected pressure of said compressed air and said volume of fuel.

13. The combustion system of claim 11 , further comprising:

a second injector system;

wherein each of said plurality of conduits define a column and two respective columns define a void therebetween;

wherein said second injector system injects a first volume of fuel into said void;

wherein said volume of compressed air exits said outlet apertures into said void to mix with said first volume of fuel; and

wherein said outlet apertures reduce a velocity head of said compressed air to assist in maintaining a selected pressure of said compressed air and said volume of fuel.

14. The turbine of claim 9 , wherein said pre-heat area includes a heat exchanger including:

a heater pathway extending along a first axis;

a cooling pathway extending along a second axis which is parallel to said first axis;

wherein said heater pathway forms a plurality of columns, spaced transversally to said first axis, and defines a plurality of channels; and

wherein said cooling pathway extends a distance along said heater pathway and generally perpendicular to said channels.

15. The turbine of claim 14 , wherein said heater pathway includes a plurality of heater tubes and said cooling pathway includes a plurality of cooling tubes.

16. The combustion system of claim 9 , further comprising:

a combustion suppressor disposed in said pre-mix to substantially eliminate any combustion of said fuel before said fuel enters said pre-heater.

17. The combustion system of claim 16 , further comprising:

a mixing area, wherein said fuel and said compressed air are mixed in said mixing area before entering said pre-heater; and

wherein said combustion suppressor includes a member disposed in said mixing area to reduce a distance of said mixing area to at least a quenching distance of said fuel.

18. The combustion system of claim 16 , further comprising:

at least two conduits spaced apart to define a mixing area;

a coating disposed on an exterior of said conduits;

wherein said fuel and said compressed air are mixed in said mixing area before entering said pre-heater; and

wherein said coating substantially inhibits combustion of said fuel.

19. A method of mixing a volume of a fuel with a volume of an oxidizer and providing said mixture to a heater with a mixer, the mixer including a conduit defining an inlet, having an inlet volume, and an outlet, having an outlet volume, spaced apart from one another, the method comprising:

flowing a fluid in a first direction in said conduit;

expressing said fluid from said conduit;

flowing said expressed fluid in a second direction at least 90 degrees to said first direction; and

maintaining a selected pressure of said fluid as it flows in said second direction.

20. The method of claim 19 , further comprising:

flowing said expressed fluid through a passage;

inhibiting a combustion of said fuel in the mixer; and

wherein said passage includes a quenching distance.

21. The method of claim 19 , further comprising:

flowing said expressed fluid through a passage defined by an exterior of said conduits; and

inhibiting a combustion of said fuel in said mixer by disposing a coating on said exterior to inhibit combustion of said fuel.

22. The method of claim 19 , wherein maintaining a selected pressure includes:

decreasing a velocity head of said oxidizer as it exits said conduit by forming said outlet area to be greater than said inlet area, wherein a lower velocity oxidizer exits said conduit than enters said conduit.

Assignments (12)