초록 ▼

An innovative cooling tube assembly is disclosed for use in cooling the liner of a combustor in a gas turbine engine. Each cooling tube has a serpentine shape that conforms to the contour of the liner as the tube extends from one end of the combustor to the other to conduct cooling air in a counterf

An innovative cooling tube assembly is disclosed for use in cooling the liner of a combustor in a gas turbine engine. Each cooling tube has a serpentine shape that conforms to the contour of the liner as the tube extends from one end of the combustor to the other to conduct cooling air in a counterflow direction to the exhaust gases. The cooling air gains heat, thereby cooling the liner wall, and is delivered in the proximity of the burners where its heat aids in combustion. An assembly of cooling tubes is provided for mounting on either the cool side or the hot side of the combustor liner, the assembly comprising a plurality of nested cooling tubes. The cooling tubes may be fabricated of a metallic material and either brazed to the liner or supported by pins inserted through the liner. The cooling tubes may also be fabricated of a CMC material by an innovative method in which an expendable mandrel of the desired cooling tube shape is inserted into one or more sleeves of a woven tubular fabric bound to a fabric shell formed in the shape of the combustor liner and densified in a furnace.

대표청구항 ▼

I claim: 1. A cooling tube for cooling a liner of a combustor chamber of a gas turbine engine, comprising: a single chamber cooling tube having a first end in fluid communication with a plenum and located proximate a rear end of the combustor chamber, the plenum supplying air to the combustor chamb

I claim: 1. A cooling tube for cooling a liner of a combustor chamber of a gas turbine engine, comprising: a single chamber cooling tube having a first end in fluid communication with a plenum and located proximate a rear end of the combustor chamber, the plenum supplying air to the combustor chamber; the single chamber cooling tube further having a second end in fluid communication with an area in proximity with a gas injector of the gas turbine engine and located proximate a front end of the combustor chamber; and a centerline extending from the first end to the second end, wherein the centerline, the first end, and the second end are non-linear when projected onto a plane; wherein the rear end of the combustor chamber and the front end of the combustor chamber are located at opposed ends of the combustor chamber for uni-directional flow of a fluid through the single chamber cooling tube, wherein the cooling tube has a serpentine shape conforming to a contour of the liner and the serpentine shape of the cooling tube allows the cooling tube to expand and contract in response to temperature gradients in the combustor chamber. 2. The serpentine cooling tube described in claim 1, wherein the cooling tube is positioned outside the combustor chamber along an exterior side of the liner. 3. A single chamber cooling tube for cooling a liner of a combustor chamber of a gas turbine engine, the single chamber cooling tube comprising: a first end of the single chamber cooling tube in fluid communication with a plenum supplying air to the combustor chamber, the first end located proximate a rear end of the combustor chamber; a second end of the single chamber cooling tube in fluid communication with an area in proximity with a gas injector of the gas turbine engine, the second end located proximate a front end of the combustor chamber, the sing chamber cooling tube positioned within the combustor chamber along an interior side of the liner, wherein the exhaust end of the combustor chamber and the intake end of the combustor chamber are located at opposed ends of the combustor chamber for uni-directional flow of a fluid through the single chamber serpentine cooling tube; and wherein the single chamber cooling tube has a serpentine shape conforming to a contour of the line and the serpentine shape of the cooling tube allows the single chamber cooling tube to expand and contract in response to temperature gradients in the combustor chamber. 4. A cooling tube assembly for cooling a liner of a combustor chamber of a gas turbine engine, the assembly comprising a plurality of single chamber serpentine cooling tubes attached to the liner, each single chamber serpentine cooling tube conforming to a contour of the liner, each single chamber serpentine cooling tube including: a first end in fluid communication with a plenum supplying air to an exhaust end of the combustor chamber, the first end located proximate the exhaust end of the combustor chamber; a second end in fluid communication with an area in proximity with a gas injector of the gas turbine engine, the second end located proximate an intake end of the combustor chamber, wherein the exhaust end of the combustor chamber and the intake end of the combustor chamber are located at opposed ends of the combustor chamber for uni-directional flow of a fluid through each of the plurality of single chamber serpentine cooling tubes; and a centerline extending from the first end to the second end, wherein the centerline, the first end, and the second end are non-linear when projected onto a plane. 5. The cooling tube assembly described in claim 4, wherein the cooling tube assembly is in contact with the liner. 6. The cooling tube assembly described in claim 4, wherein the cooling tube assembly is maintained at a spaced distance from the liner. 7. The cooling tube assembly described in claim 4, wherein the plurality of single chamber serpentine cooling tubes is positioned on an exterior side of the liner. 8. The cooling tube assembly described in claim 4, wherein the serpentine shape of each tube is formed as a plurality of alternating convex and concave bends along a length of each tube. 9. A cooling tube assembly for cooling a liner of a combustor chamber of a gas turbine engine, the assembly comprising a plurality of single chamber serpentine cooling tubes attached to the liner, each serpentine cooling tube conforming to a contour of the liner, each single chamber serpentine cooling tube having a first end in fluid communication with a plenum located proximate an exhaust end of the combustor chamber, each single chamber serpentine cooling tube having a second end in fluid communication with an area in proximity with a gas injector of the gas turbine engine located proximate an intake end of the combustor chamber, wherein the exhaust end of the combustor chamber and the intake end of the combustor chamber are located at opposed ends of the combustor chamber for uni-directional flow of a fluid through each of the plurality of single chamber serpentine cooling tubes, each single chamber serpentine cooling tube supported by a plurality of pins to maintain the serpentine cooling tube at a spaced distance from the liner and each pin having a proximal end attached to the simile chamber serpentine cooling tube and a distal end inserted through a hole in the liner, the distal end being secured from removal from the hole in a manner allowing rotational movement of the pin within the hole. 10. The cooling tube assembly described in claim 9, wherein: each single chamber serpentine cooling tube is fabricated of a metallic material; and each proximal end is secured to the single chamber serpentine cooling tube by brazing. 11. The cooling tube assembly described in claim 9, wherein the plurality of single chamber serpentine cooling tubes is positioned on an interior side of the liner. 12. A method of cooling a combustor liner, comprising: diverting a portion of an incoming pressurized gas stream entering an intake end of the combustor to a plenum located proximate an exhaust end of the combustor; directing the pressurized gas stream from the plenum through a plurality of single chamber serpentine cooling tubes aligned along a surface of the combustor liner, each single chamber serpentine cooling tube having a first end in fluid communication with the plenum and located proximate and exhaust end of the combustor, a second end in fluid communication with an area proximate with a fuel atomizer and located proximate the intake end of the combustor, and a centerline extending from the first end to the second end, wherein the centerline, the first end, and the second end are non-linear when projected onto a plane and wherein the exhaust end of the combustor and the intake end of the combustor are located at opposed ends of the combustor liner for uni-directional flow of a fluid through each of the plurality of single chamber serpentine cooling tubes; allowing the pressurized gas stream flowing through the single chamber serpentine cooling tubes to absorb heat from the combustor wall to heat the pressurized gas stream to form a heated gas stream; and providing the heated gas stream exiting the second ends to the fuel atomizer, whereby the heated gas stream aids combustion. 13. The method of cooling a combustor liner described in claim 12, wherein the plurality of single chamber serpentine cooling tubes is aligned along an interior surface of the combustor liner. 14. The method of cooling a combustor liner described in claim 13, wherein the plurality of single chamber serpentine cooling tubes is comprised of a metallic material, and wherein each cooling tube is supported by a plurality of pins maintaining the cooling tube a spaced distance from the liner, each pin having a proximal end attached to the cooling tube and a distal end inserted through a hold in the liner, the distal end being secured from removal from the hole in a manner allowing rotational movement of the pin within the hole. 15. The method of cooling a combustor liner described in claim 12, wherein the plurality of single chamber serpentine cooling tubes is aligned along an exterior surface of the combustor liner. 16. A method of cooling a combustor liner, comprising: diverting a portion of an incoming pressurized gas stream entering an intake end of the combustor to a plenum located proximate an exhaust end of the combustor; directing the pressurized gas stream from the plenum through a plurality of single chamber serpentine cooling tubes aligned along a surface of the combustor liner, each single chamber serpentine cooling tube comprised of a ceramic matrix composite material and having a first end in fluid communication with the plenum and located proximate and exhaust end of the combustor, a second end in fluid communication with an area proximate with a fuel atomizer and located proximate the intake end of the combustor, and a centerline extending from the first end to the second end, wherein the centerline, the first end, and the second end are non-linear when projected onto a plane and wherein the exhaust end of the combustor and the intake end of the combustor are located at opposed ends of the combustor liner for uni-directional flow of a fluid through each of the plurality of single chamber serpentine cooling tubes; allowing the pressurized gas stream flowing through the single chamber serpentine cooling tubes to absorb heat from the combustor wall to heat the pressurized gas stream to form a heated gas stream; and providing the heated was stream exiting the second ends to the fuel atomizer, whereby the heated gas stream aids combustion.