Operability geared turbofan engine including compressor section variable guide vanes

Patent metadata

Field	Value
Publication number	US-11280271-B2
Application number	US-201314433444-A
Country	US
Kind code	B2
Filing date	Oct 3, 2013
Priority date	Oct 9, 2012
Publication date	Mar 22, 2022
Grant date	Mar 22, 2022

Abstract

A gas turbine engine has a fan which includes a plurality of fan blades that are rotatable about an axis, and a compressor section, where the combustor section includes a first compressor and a second compressor aft of the first compressor. At least one first variable guide vane controls operation of the first compressor and at least one second variable guide vane controls operation of the second compressor. A combustor is in fluid communication with the compressor section and a turbine section is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a fan including a plurality of fan blades rotatable about an axis;
a compressor section, wherein the compressor section includes a first compressor and a second compressor aft of the first compressor with at least one first variable guide vane controlling operation of the first compressor and at least one second variable guide vane controlling operation of the second compressor, wherein the pressure ratio of the first compressor is in the range of 4:1 to 7:1, and the pressure ratio of the second compressor is in the range 8:1 to 15:1;
a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor, wherein the turbine section includes a first turbine and a second turbine arranged aft of the first turbine; and
a geared architecture driven by the turbine section for rotating the fan about the axis; and
wherein the fan has a total number of the fan blades, the total number of the fan blades being less than 20, and a ratio between the total number of the fan blades and a total number of turbine rotors of the second turbine is between 3.3 and 8.6.

2. The gas turbine engine according to claim 1 , wherein the compressor section includes an overall pressure ratio in the range of 40:1 to 70:1.

3. The gas turbine engine according to claim 1 , wherein the first compressor and the second turbine mounted to a first spool, and the second compressor and the first turbine mounted on a second spool.

4. The gas turbine engine according to claim 3 , wherein the geared architecture is coupled between the first spool and the fan section.

5. The gas turbine engine according to claim 4 , comprising:
multiple stages of first variable guides in the first compressor;
multiple stages of second variable guides in the second compressor; and
wherein the compressor section includes an overall pressure ratio in the range of 40:1 to 70:1.

6. The gas turbine engine according to claim 5 , wherein the second turbine includes at least 3 turbine rotors but no more than 6 turbine rotors.

7. The gas turbine engine according to claim 6 , wherein the at least one first variable guide vane coupled to a first actuator, and the at least one second variable guide vane coupled to a second actuator, and further comprising a controller coupled to the first actuator and the second actuator, the controller operable to cause the first actuator to move the at least one first variable guide vane, and the controller operable to cause the second actuator to move the at least one second variable guide vane.

8. The gas turbine engine according to claim 7 , wherein the second turbine includes 5 turbine rotors.

9. The gas turbine engine according to claim 8 , wherein the at least one first variable guide vane and the at least one second variable guide vane are independently adjustable.

10. The gas turbine engine according to claim 1 , wherein the geared architecture is arranged forward of the combustor.

11. The gas turbine engine according to claim 1 , comprising multiple stages of first variable guides in the first compressor.

12. The gas turbine engine according to claim 11 , comprising multiple stages of second variable guides in the second compressor.

13. The gas turbine engine according to claim 1 , comprising multiple stages of second variable guides in the second compressor.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Levasseur Glenn
• Suciu Gabriel L
• Stetson Gary M

Classifications

• F01D17/162

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F05D2260/4031

  as in toothed gearing · CPC title

• F02C9/20

  by throttling; by adjusting vanes · CPC title

• F02C7/36 Primary

  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

• F02C7/32

  Arrangement, mounting, or driving, of auxiliaries · CPC title