Turbine section of high bypass turbofan

Patent metadata

Field	Value
Publication number	US-11346289-B2
Application number	US-202016881567-A
Country	US
Kind code	B2
Filing date	May 22, 2020
Priority date	Aug 1, 2007
Publication date	May 31, 2022
Grant date	May 31, 2022

Abstract

A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.

First claim

What is claimed is:

1. A turbofan engine comprising:
an engine case;
a gaspath through the engine case;
a fan having a circumferential array of fan blades;
a compressor in fluid communication with the fan;
a combustor in fluid communication with the compressor;
a turbine in fluid communication with the combustor, the turbine having a two-stage high pressure turbine section coupled to drive a portion of the compressor and a low pressure turbine section; and
a speed reduction mechanism coupling the low pressure turbine section to the fan, wherein the speed reduction mechanism comprises gearbox coupled to the fan and rotatable by the low pressure turbine section such that the low pressure turbine section rotates faster than the fan, the gear box having a speed reduction ratio between 2:1 and 13:1,

wherein: a maximum gaspath radius along the low pressure turbine section to a maximum radius of the fan is greater than 0.35 and less than 0.55; and
a ratio of a low pressure turbine section airfoil count to a bypass area ratio is less than 170.

2. The engine of claim 1 further comprising:
a fan case encircling the fan blades radially outboard of the engine case.

3. The engine of claim 1 wherein:
a hub-to-tip ratio (R I :R O ) of the low pressure turbine section is between 0.4 and 0.5 measured at the maximum R O axial location in the low pressure turbine section.

4. The engine of claim 3 wherein:
an airfoil count of the low pressure turbine section is below 1600.

5. The engine of claim 1 wherein:
said ratio of low pressure turbine section airfoil count to bypass area ratio is between 10 and 150.

6. The engine of claim 1 wherein:
the compressor comprises:
a low pressure compressor section; and
a high pressure compressor section.

7. The engine of claim 6 wherein:
the turbine has a high pressure turbine section coupled to drive the high pressure compressor section.

8. The engine of claim 7 wherein:
there are no additional compressor or turbine sections.

9. The engine of claim 6 wherein:
blades of the low pressure compressor section and low pressure turbine section share a shaft; and
the speed reduction mechanism comprises an epicyclic transmission that couples the shaft to a fan shaft to drive the fan with a speed reduction.

10. The engine of claim 1 wherein:
the speed reduction mechanism comprises an epicyclic transmission.

11. The engine of claim 1 wherein:
the low pressure turbine section has 2 to 6 blade stages.

12. The engine of claim 1 wherein:
an airfoil count of the low pressure turbine section is below 1600.

13. The engine of claim 1 in combination with a mounting arrangement wherein an aft mount reacts at least a thrust load.

14. The engine of claim 1 wherein:
the low pressure turbine section has blade stages interspersed with vane stages.

Assignees

• Raytheon Tech Corp

Inventors

• Adams Paul R
• Schwarz Frederick M
• Magge Shankar S
• Staubach Joseph B
• Lord Wesley K
• Suciu Gabriel L

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F02C3/107 Primary

  with two or more rotors connected by power transmission · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F02C7/36

  Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) · CPC title

• F02C7/20

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title