Fan and low pressure compressor geared to low speed spool of gas turbine engine
A gas turbine engine may include a high speed spool, a low speed spool, a first epicyclic gear system, and a second epicyclic gear system. Generally, the high speed spool mechanically connects a high pressure turbine to a high pressure compressor, and the low speed spool mechanically connects a low pressure turbine to at least one of a fan and a prop via the first epicyclic gear system and to a low pressure compressor via the second epicyclic gear system, according to various embodiments. The first epicyclic gear system and the second epicyclic gear system may include a common sun gear shaft.
1. A gas turbine engine comprising:
a high speed spool mechanically connecting a high pressure turbine to a high pressure compressor;
a first epicyclic gear system comprising a static first ring gear;
a second epicyclic gear system comprising a static second ring gear; and
a low speed spool mechanically connecting a low pressure turbine to at least one of a fan and a prop via the first epicyclic gear system and to a low pressure compressor via the second epicyclic gear system;
wherein both the static first ring gear and the static second ring gear are coupled to a common static support structure, wherein the at least one of the fan and the prop as well as the low pressure compressor are rotatably supported, via one or more bearings, by the common static support structure.
2. The gas turbine engine of claim 1 , wherein the first epicyclic gear system and the second epicyclic gear system comprise a common sun gear shaft.
3. The gas turbine engine of claim 2 , wherein the common sun gear shaft comprises a first portion that is forward of a second portion, wherein the first portion is mechanically connected to the first epicyclic gear system and the second portion is mechanically connected to the second epicyclic gear system.
4. The gas turbine engine of claim 3 , wherein the first portion has a different radius than the second portion.
5. The gas turbine engine of claim 1 , wherein the static first static ring gear is directly mechanically coupled to the common static support structure.
6. The gas turbine engine of claim 5 , wherein the static second ring gear is mechanically coupled to a portion of a structural case disposed between the low pressure compressor and the high pressure compressor.
7. The gas turbine engine of claim 6 , wherein the common static support structure is coupled to the structural case via a support member that extends between the low pressure compressor and the at least one of the fan and the prop.
8. The gas turbine engine of claim 1 , wherein the common static support structure is parallel to an engine central longitudinal axis of the gas turbine engine.
9. The gas turbine engine of claim 1 , wherein the at least one of the fan and the prop is the fan, wherein the fan and the low pressure compressor are configured to rotate in a same direction.
10. The gas turbine engine of claim 1 , wherein the first epicyclic gear system is a planetary-type system.
11. The gas turbine engine of claim 10 , wherein: the at least one of the fan and the prop is the fan; the first epicyclic gear system comprises a gear carrier mounted to intermediate gears; and the fan is coupled to the gear carrier.
12. A gas turbine engine comprising:
a high speed spool mechanically connecting a high pressure turbine to a high pressure compressor;
a first epicyclic gear system comprising a static first ring gear;
a second epicyclic gear system comprising a static second ring gear; and
a low speed spool mechanically connecting a low pressure turbine to at least one of a fan and a prop via the first epicyclic gear system and to a low pressure compressor via the second epicyclic gear system;
wherein the first epicyclic gear system and the second epicyclic gear system comprise a common sun gear shaft, wherein the common sun gear shaft comprises a first portion that is forward of a second portion, wherein the first portion is mechanically connected to the first epicyclic gear system and the second portion is mechanically connected to the second epicyclic gear system; and
wherein both the static first ring gear and the static second ring gear are coupled to a common static support structure, wherein the at least one of the fan and the prop as well as the low pressure compressor are rotatably supported, via one or more bearings, by the common static support structure.
13. The gas turbine engine of claim 12 , wherein the static first static ring gear is directly mechanically coupled to the common static support structure.
14. The gas turbine engine of claim 13 , wherein the static second ring gear is mechanically coupled to a portion of a structural case disposed between the low pressure compressor and the high pressure compressor.
15. The gas turbine engine of claim 14 , wherein the common static support structure is coupled to the structural case via a support member that extends between the low pressure compressor and the at least one of the fan and the prop.
16. A method of operating a gas turbine engine, the method comprising: operating at least one of a fan and a prop at a first operating speed; operating a low pressure compressor at a second operating speed; wherein the at least one of the fan and the prop and the low pressure compressor are mechanically connected to a low speed spool of the gas turbine engine via a first epicyclic gear system and a second epicyclic gear system, respectively;
wherein both the first epicyclic gear system and the second epicyclic gear system comprise static ring gears.