GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION AND BEARING SUPPORT FEATURES

摘要

A turbine section of a gas turbine engine according to an example of the present disclosure includes, among other things, a fan drive turbine section and a second turbine section. The fan drive turbine section has a first exit area at a first exit point and is configured to rotate at a first speed. The second turbine section has a second exit area at a second exit point and is configured to rotate at a second speed, which is faster than the first speed.

主权项

1. A turbine section of a gas turbine engine, comprising:
a fan drive turbine section; and a second turbine section, wherein said fan drive turbine section has a first exit area at a first exit point and is configured to rotate at a first speed, wherein said second turbine section has a second exit area at a second exit point and is configured to rotate at a second speed, which is faster than the first speed, wherein a first performance quantity is defined as the product of the first speed squared and the first area, wherein a second performance quantity is defined as the product of the second speed squared and the second area, wherein a ratio of the first performance quantity to the second performance quantity is between about 0.5 and about 1.5, and wherein said second turbine section is configured to drive a first shaft supported by a first bearing, said fan drive turbine is configured to drive a second shaft supported by a second bearing, and said first and second bearings are situated between said first exit area and said second exit area.