Combustor for a low-emissions gas turbine engine
First Claim
1. A combustor for a gas turbine engine, said combustor comprising:
- a combustor cooling shield;
a combustor liner having an inlet portion and an outlet portion, said combustor liner being positioned within said combustor cooling shield, said combustor liner being connected with said combustor cooling shield at said outlet portion, said combustor liner having a hot side and a cold side, said cold side and said combustor cooling shield defining a cooling channel therebetween, said hot side defining a combustion zone therein, said combustion zone being adapted to receive compressed air and a fuel at said inlet portion, said combustion zone being adapted to exhaust a combustion gas into a turbine being in fluid communication with said outlet portion, said cooling channel being.adapted to receive a compressed air stream; and
a plurality of concavities disposed on said cold side, said concavities being adapted to increase convective cooling of said combustor liner.
1 Assignment
0 Petitions
Accused Products
Abstract
Many government entities regulated emission from gas turbine engines including CO. CO production is generally reduced when CO reacts with excess oxygen at elevated temperatures to form CO2. Many manufactures use film cooling of a combustor liner adjacent to a combustion zone to increase durability of the combustion liner. Film cooling quenches reactions of CO with excess oxygen to form CO2. Cooling the combustor liner on a cold side (backside) away from the combustion zone reduces quenching. Furthermore, placing a plurality of concavities on the cold side enhances the cooling of the combustor liner. Concavities result in very little pressure reduction such that air used to cool the combustor liner may also be used in the combustion zone. An expandable combustor housing maintains a predetermined distance between the combustor housing and combustor liner.
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Citations
24 Claims
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1. A combustor for a gas turbine engine, said combustor comprising:
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a combustor cooling shield; a combustor liner having an inlet portion and an outlet portion, said combustor liner being positioned within said combustor cooling shield, said combustor liner being connected with said combustor cooling shield at said outlet portion, said combustor liner having a hot side and a cold side, said cold side and said combustor cooling shield defining a cooling channel therebetween, said hot side defining a combustion zone therein, said combustion zone being adapted to receive compressed air and a fuel at said inlet portion, said combustion zone being adapted to exhaust a combustion gas into a turbine being in fluid communication with said outlet portion, said cooling channel being.adapted to receive a compressed air stream; and a plurality of concavities disposed on said cold side, said concavities being adapted to increase convective cooling of said combustor liner. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14)
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15. A method for improved cooling of a combustor for a gas turbine engine comprising the steps of:
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positioning a combustor liner having a cold side inside a combustor cooling shield with said cold side facing said combustor cooling shield; establishing a predetermined distance between said combustor cooling shield and said cold side, said predetermined distance, said cooling shield, and said cold side defining a cooling channel; and maintaining said predetermined distance in response to expansion and contraction of said combustor liner. - View Dependent Claims (16, 17, 18, 19, 20, 21)
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22. A method for reducing emissions of a gas turbine engine comprising the steps of:
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directing a volume of air having a first pressure to a combustor, said combustor having a combustor cooling shield, a combustor liner, and a cooling channel between said combustor cooling shield and said combustor liner, said combustor liner having an inlet portion, an outlet portion, and a plurality of concavities adjacent said combustor cooling shield, said concavities being adapted to retard growth of a thermal boundary layer; diverting a first portion of said volume of air into said cooling channel intermediate said inlet portion and said outlet portion; diverting a remainder of said volume of air into said inlet portion; passing said first portion over said concavities, said first portion convectively cooling said combustor liner; and directing said first portion into said inlet portion, said first portion being at a second pressure wherein said second pressure being about equal to said first pressure. - View Dependent Claims (23, 24)
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Specification