Gas turbine engine variable pitch fan blade
A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan rotatable about an engine axis with a plurality of fan blades rotatable about a fan blade axis. A geared architecture is in communication with the fan and driven by a turbine section. The fan rotates at a first speed and the turbine section rotates at a second speed different from the first speed and a fixed area fan nozzle in communication with the fan section.
1. A gas turbine engine comprising:
a fan section including a fan rotatable about an engine axis with a plurality of fan blades rotatable about a fan blade axis, wherein at least a portion of each of the plurality of fan blades is radially aligned with a portion of a core flow path, each of the plurality of fan blades are rotatably attached to a central disk, a radially inner end of each of the plurality of fan blades are attached to a rotatable mount on to the central disk, and each of the plurality of fan blades rotate no more than 20 degrees;
a geared architecture in communication with the fan and driven by a turbine section, wherein the fan rotates at a first speed and the turbine section rotates at a second speed different from the first speed; and
a fixed area fan nozzle in communication with the fan section.
2. The gas turbine engine of claim 1 , wherein each of the plurality of fan blades are attached to the central disk and the central disk is located entirely axially spaced upstream of the geared architecture.
3. The gas turbine engine of claim 1 , wherein the plurality of fan blades are located fluidly upstream of the core flow path of the gas turbine engine.
4. A gas turbine engine comprising:
a fan section including a fan rotatable about an engine axis with a plurality of fan blades rotatable about a fan blade axis, wherein the plurality of fan blades are located upstream of a core flow path of the gas turbine engine, each of the plurality of fan blades are rotatably attached to a central disk, a radially inner end of each of the plurality of fan blades are attached to a rotatable mount on to the central disk, and each of the plurality of fan blades rotate no more than 20 degrees.
5. The gas turbine engine of claim 4 , wherein the geared architecture includes a geared architecture is driven by a turbine section and rotates the fan about the engine axis.
6. The gas turbine engine of claim 4 , including a low pressure turbine section with at least three sections.
7. The gas turbine engine of claim 6 , wherein the low pressure turbine section includes no more than six sections.
8. The gas turbine engine of claim 4 , including a fixed area fan nozzle in communication with the fan section.
9. The gas turbine engine of claim 4 , wherein the engine axis is substantially perpendicular to the fan blade axis.
10. The gas turbine engine of claim 4 , wherein the fan blade axis of each of the plurality of fan blades intersects the engine axis at substantially an intersection point C.
11. The gas turbine engine of claim 4 , wherein the central disk is located entirely axially upstream of the geared architecture.
12. The gas turbine engine of claim 4 , wherein at least a portion of each of the plurality of fan blades is radially aligned with a portion of the core flow path.
13. A method of operating a gas turbine engine comprising the steps of:
rotating a fan section including a plurality of fan blades at a first speed, wherein the plurality of fan blades direct air into a core flow path of the gas turbine engine;
rotating the plurality of fan blades about a fan blade axis no more than 20 degrees to change each of the fan blades from a common first pitch to a common second pitch; and
rotating a low pressure turbine section at a second speed, wherein the first speed is different from the second speed, wherein the fan section includes a fan rotatable about an engine axis with the plurality of fan blades rotatable about the fan blade axis, at least a portion of each of the plurality of fan blades is radially aligned with a portion of a core flow path, each of the plurality of fan blades are rotatably attached to a central disk, a radially inner end of each of the plurality of fan blades are attached to a rotatable mount on to the central disk.
14. The method of claim 13 , wherein an axis of rotation of the gas turbine engine is substantially perpendicular to the fan blade axis.
15. The method of claim 13 , wherein the low pressure turbine section includes at least three section and no more than six sections.
16. The method of claim 13 , wherein the plurality of fan blades are located fluidly upstream of the core flow path and a portion of the air being directed into the core flow path travels over a platform of each of the plurality of fan blades.