Geared turbofan engine with a high ratio of thrust to turbine volume
AssigneeRaytheon Technologies Corporation
InventorsFrederick M. Schwarz, Daniel Bernard Kupratis
Life of this patent
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Abstract
A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in the first direction.
Claims30
A gas turbine engine turbine comprising:
- a high pressure turbine configured to rotate with a high pressure compressor about a central axis;
- a low pressure turbine configured to rotate with a low pressure compressor about said central axis;
- a fan having a plurality of fan blades and connected to the low pressure turbine via a gear reduction,
- wherein the gas turbine engine is configured to have a power ratio of a thrust provided by said engine, to a volume of a turbine section including both said high pressure turbine and said low pressure turbine that is greater than or equal to 3.0 and less than or equal to 5.5 lbf/in3;
- said thrust is sea level take-off, flat-rated static thrust;
- said fan being received within a fan housing, and said high pressure turbine, said high pressure compressor, said low pressure compressor and said low pressure turbine all received within a core housing, a bypass duct defined between said fan housing and said core housing, and said fan delivering air into said bypass duct as propulsion air, and into said core housing, a bypass ratio being defined as a ratio of a volume of air delivered into said bypass duct compared to a volume of air delivered into said core housing, and said bypass ratio being greater than 10.0;
- and
- a mid-turbine frame positioned intermediate said high pressure turbine and said low pressure turbine, said mid-turbine frame including a bearing, wherein said bearing support said high pressure turbine, and said mid-turbine frame including airfoils in a core airflow path that provide inlet stator vanes to turn a flow to feed a first blade row of said low pressure turbine.
The gas turbine engine as set forth in 1, wherein said low pressure turbine having a pressure ratio greater than 5.0, defined by a total pressure measured prior to an inlet of said low pressure turbine as related to a pressure at an outlet of said low pressure turbine prior to an exhaust nozzle.
The gas turbine engine as set forth in 16, wherein said low pressure turbine having a pressure ratio greater than 5.0, defined by a total pressure measured prior to an inlet of said low pressure turbine as related to a pressure at an outlet of said low pressure turbine prior to an exhaust nozzle.
A gas turbine engine turbine comprising:
- a high pressure turbine configured to rotate with a high pressure compressor about a central axis;
- a low pressure turbine configured to rotate with a low pressure compressor about said central axis;
- a fan having a plurality of fan blades and connected to the low pressure turbine via a gear reduction,
- wherein the gas turbine engine is configured to have a power ratio of a thrust provided by said engine, to a volume of a turbine section including both said high pressure turbine and said low pressure turbine that is greater than or equal to 1.5 and less than or equal to 5.5 lbf/in3;
- said thrust is sea level take-off, flat-rated static thrust;
- said fan being received within a fan housing, and said high pressure turbine, said high pressure compressor, said low pressure compressor and said low pressure turbine all received within a core housing, a bypass duct defined between said fan housing and said core housing, and said fan delivering air into said bypass duct as propulsion air, and into said core housing, a bypass ratio being defined as a ratio of a volume of air delivered into said bypass duct compared to a volume of air delivered into said core housing, and said bypass ratio being greater than 10.0;
- and
- wherein blades in a first row of said low pressure turbine being at least one of directionally solidified cast blades, a single crystal cast blade, or a hollow internally cooled blade.
The gas turbine engine as set forth in 18, wherein said low pressure turbine having a pressure ratio greater than 5.0, defined by a total pressure measured prior to an inlet of said low pressure turbine as related to a pressure at an outlet of said low pressure turbine prior to an exhaust nozzle.
Dependencies are inferred from the claim text.