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US 2019/0293291 A1Published application
Cooling features for a gas turbine engine
AssigneeSiemens Aktiengesellschaft
InventorsTimothy A. Fox, Jacob William Hardes
Life of this patent
Estimating the term…
Abstract
A gas turbine engine has a converging duct that has combustion products flow at low mach speeds through a first portion and a high mach speeds through a second portion. The converging duct has two types of cooling schemes formed. One type of cooling scheme is beneficial for the low mach speed combustion product flow and one type of cooling scheme is beneficial for the high mach speed combustion product flow. The two cooling schemes are blended together in order increase the efficiency of the cooling of the converging duct.
Claims20
A gas turbine engine comprising:
- a combustor;
- a converging duct connected to the combustor, wherein the converging duct comprises;
- a first portion having a first portion layer, wherein the first portion has a first diameter, wherein the first portion layer has formed thereon cooling channels for cooling the first portion, wherein the cooling channels extend axially from upstream to downstream;
- a second portion having a second portion layer, wherein the second portion has a second diameter smaller than the first diameter, wherein the second portion layer has formed thereon high mach cooling features for the second portion;
- and
- wherein effusion holes are formed in the cooling channels at a location proximate to the second portion layer.
3 more elements
A converging duct comprising:
- a first portion having a first portion layer, wherein the first portion has a first diameter, wherein the first portion layer has formed thereon cooling channels for cooling the first portion, wherein the cooling channels extend axially from upstream to downstream;
- a second portion having a second portion layer, wherein the second portion has a second diameter smaller than the first diameter, wherein the second portion layer has formed thereon high mach cooling features for cooling the second portion;
- and
- wherein effusion holes are formed in the cooling channels at a location proximate to the second portion layer.
1 more element
Dependencies are inferred from the claim text.