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US 11,448,123 B2Granted
Geared turbofan architecture
AssigneeRaytheon Technologies Corporation
InventorsFrederick M. Schwarz, Daniel Bernard Kupratis
Life of this patent
Estimating the term…
Abstract
A gas turbine engine includes a fan bypass ratio greater than 12. A speed reduction device includes a gear ratio of at least 2.6. A turbine section includes a transition duct that is located between a high pressure turbine and a low pressure turbine and includes fewer support struts than vanes in a first vane row of the low pressure turbine.
Claims17
A gas turbine engine comprising:
- a fan section having a fan bypass ratio greater than 12 and less than 20;
- a speed reduction device drivingly connected to the fan section;
- a compressor section with a high pressure compressor having between 8 and 13 stages and a pressure ratio of at least 16:1 and less than 35:1;
- and
- a turbine section including a transition duct located between a high pressure turbine and a low pressure turbine including fewer support struts than vanes in a first vane row of the low pressure turbine, wherein the first vane row of the low pressure turbine is located downstream of the transition duct and downstream of a first row of blades in the low pressure turbine, wherein the first row of blades in the low pressure turbine are immediately downstream of the support struts.
2 more elements
A method of designing a gas turbine engine for improved performance comprising:
- positioning a transition duct between a high pressure turbine and a low pressure turbine, wherein the transition duct includes fewer support struts than vanes in a first vane row of the low pressure turbine and the first vane row of the low pressure turbine is located downstream of the transition duct and a first row of blades in the low pressure turbine are immediately downstream of the support struts;
- decreasing a design temperature in the transition duct by increasing a pressure ratio in a high pressure compressor in a compressor section and increasing extraction from a working fluid with the high pressure turbine;
- and
- wherein the gas turbine engine includes a fan section having a fan bypass ratio greater than 12 and less than 20 and a speed reduction device drivingly connected to the fan section.
1 more element
Dependencies are inferred from the claim text.