Combustor cooling for gas turbine engines

• US 5,694,761 A
• Filed: 10/31/1995
• Issued: 12/09/1997
• Est. Priority Date: 07/07/1993
• Status: Expired due to Fees

• Current Assignee: Arthur T. Griffin Jr
• Original Assignee: Arthur T. Griffin Jr
• Inventors: Griffin, Arthur T. Jr.
• Primary Examiner(s): Casaregola, Louis J.
• Application Number:
  US08/550,893
• Time in Patent Office: 770 Days
• Field of Search: 60/39.05, 60/39.55, 60/39.511
• US Class Current: 60/775
• CPC Class Codes: F01K 21/047 having at least one combustion gas turbine
• CPC Class Codes: F02C 3/30 Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases F02C7/141, F02C7/30, F01D21/00, F01K21/04, F23D11/10 take precedence
• CPC Class Codes: F02C 7/141 of working fluid
• CPC Class Codes: F05D 2260/2322 steam
• CPC Class Codes: F23L 2900/07009 Injection of steam into the combustion chamber
• CPC Class Codes: F23M 5/08 Cooling thereof; Tube walls
• CPC Class Codes: F23R 3/005 Combined with pressure or heat exchangers

Abstract

A gas turbine engine assembly including improved means for cooling the combustor to preclude thermal failure of the combustor and to preclude NO_x formation. The system includes a liquid pump driven by the turbine shaft and supplying a cooling fluid to an annular chamber defined around the central combustion chamber of the combustor. The cooling fluid is thereby placed in heat exchange relation to the combustor to absorb heat from the combustion products within the combustion chamber and convert the fluid to a relatively higher energy condition, whereafter the fluid in its high energy condition is injected into the combustion chamber for mixture with the combustion products and delivery with the combustion products to the turbine inlet. The cooling liquid may totally fill the annular cooling chamber around the combustion chamber or may partially fill the cooling chamber, or the cooling fluid arriving at the cooling chamber may already be in a gaseous state so that the cooling chamber is totally filled with a vapor.

Claims

1. A method of cooling a combustor and combustion gases of a gas turbine engine assembly of the type including a turbine with an inlet and with a discharge of combustion products, said combustor defining a combustion chamber and including a burner disposed adjacent to one end of said combustion chamber, said burner arranged to receive a pressurized fuel/air mixture and generate products of combustion within said burner for delivery to said turbine through said combustion chamber, the method comprising:

providing a substance in a first energy phase by a pump driven by said gas turbine;

placing said substance in heat exchange relation to said discharge of said turbine to convert said substance to a second energy phase;

placing said substance in heat exchange relation to an apparatus to convert said substance to a third energy phase;

delivering said substance to said one end of said combustion chamber at its third energy phase;

placing said substance at said third energy phase in heat exchange relation to said combustion chamber to absorb energy from said combustion products within said combustion chamber and converting said substance to a fourth energy phase; and

injecting said substance in its fourth energy phase into said combustion chamber proximate the opposite end of said combustion chamber for mixture with said combustion products and delivery with said combustion products to said turbine inlet.

2. A method according to claim 1 wherein:

said combustor has an annular cooling chamber in surrounding relation to said combustion chamber and having apertures communicating with said combustion chamber;

said step of placing said substance at said third energy phase in heat exchange relation with said combustion chamber comprises delivering said substance at said third energy phase to said annular cooling chamber;

said conversion of said substance to its fourth energy phase occurs in said annular cooling chamber; and

said step of injecting said substance in its fourth energy phase into said combustion chamber comprises passing the substance through said apertures and into said combustion chamber.

3. A method according to claim 1 wherein:

said first energy phase is a first temperature liquid phase;

said second energy phase is a second temperature liquid phase said second temperature liquid phase being at a higher temperature than said first temperature liquid phase;

said third energy phase is a first temperature gas phase; and

said fourth energy phase is a second temperature gas phase, said second temperature gas phase being at a higher temperature than said first temperature gas phase.

4. A method according to claim 1 wherein:

said third energy phase is a low temperature gas phase; and

said fourth energy phase is a higher temperature gas phase.

5. A combustor for generating combustion products for delivery to a gas turbine, said combustor comprising:

a central combustion chamber defining a central axis;

a burner disposed adjacent to one end of said central combustion chamber to deliver products of combustion to said one end of said central combustion chamber;

a source of combustion air;

a combustion air compressor disposed between said source of combustion air and said burner;

a source of fuel;

a fuel compressor disposed between said source of fuel and said burner;

a discharge at the opposite end of said central combustion chamber for delivering combustion products to said turbine;

an annular cooling chamber in surrounding relation to said central combustion chamber;

an entry opening in said annular cooling chamber for receipt of a cooling gas, said cooling gas forming a bath within said annular cooling chamber to absorb thermal energy from said combustion products within said central combustion chamber; and

a plurality of apertures providing communication between said annular cooling chamber and said central combustion chamber proximate said opposite end of said central combustion chamber.

6. A combustor according to claim 5 wherein:

said entry opening in said annular cooling chamber is adjacent to said one end of said central combustion chamber.

7. A combustor according to claim 6 wherein:

said apertures are provided in an annular region extending from a mid-region of said combustion chamber central to said opposite end of said central combustion chamber.

8. A gas turbine assembly comprising:

a turbine having an inlet for combustion products and a combustion product discharge, said turbine driving a turbine shaft;

a combustor operative to generate products of combustion for delivery to said turbine inlet, said combustor comprising;

a combustion chamber;

a burner disposed adjacent to one end of said combustion chamber to deliver products of combustion to said one end of said combustion chamber;

a discharge at the opposite end of said combustion chamber for delivering combustion products to said turbine inlet;

an annular cooling chamber in surrounding relation to said combustion chamber;

an entry opening in said annular cooling chamber for receipt of a cooling gas, said cooling gas forming a bath within said annular cooling chamber to absorb thermal energy from said combustion products within said combustion chamber;

a plurality of apertures providing communication between said annular cooling chamber and said combustion chamber proximate said opposite end of said combustion chamber;

a source of combustion air;

a combustion air compressor disposed between said source of combustion air and said burner;

a source of fuel;

a fuel compressor disposed between said source of fuel and said burner;

a source of liquid cooling fluid;

a heat exchanger disposed between said source of liquid cooling fluid and said combustion chamber, said heat exchanger delivering thermal energy to said liquid cooling fluid to create said cooling gas;

a pump driven by said turbine shaft, having an inlet connected to said source of cooling fluid, and having an outlet connected to said heat exchanger for delivering said cooling fluid to said heat exchanger in a liquid phase.

9. A gas turbine engine assembly according to claim 8 wherein:

said heat exchanger for delivering thermal energy comprises a boiler.

10. The gas turbine engine assembly according to claim 8 wherein one of said combustion air compressor and said fuel compressor is driven by said turbine shaft.

11. The gas turbine engine assembly according to claim 10 wherein the other of said combustion air compressor and said fuel compressor is driven by said turbine shaft.