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:
one of a fan or a prop;
a low pressure compressor;
a high speed spool mechanically connecting a high pressure turbine to a high pressure compressor;
a first epicyclic gear system;
a second epicyclic gear system; and
a low speed spool mechanically connecting a low pressure turbine to one of the fan or the prop via the first epicyclic gear system and to the low pressure compressor via the second epicyclic gear system, the low speed spool comprising a forward section defining a sun gear shaft for both the first epicyclic gear system and the second epicyclic gear system, wherein:
the low pressure compressor is immediately aft of the one of the fan or the prop,
the first epicyclic gear system, the second epicyclic gear system, the one of the fan or the prop, and the low pressure compressor are mounted to a common static support structure, and
the low speed spool is configured to drive the first epicyclic gear system and the second epicyclic gear system via the sun gear shaft.
2. 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.
3. The gas turbine engine of claim 2 , wherein the common static support structure is mounted to a structural case aft of the one of the fan or the prop and the low pressure compressor, but forward of the high pressure compressor.
4. The gas turbine engine of claim 1 , wherein the one of the fan or the prop is the fan, and wherein the fan and the low pressure compressor are configured to rotate in opposite directions.
5. The gas turbine engine of claim 1 , wherein the second epicyclic gear system is a star system.
6. The gas turbine engine of claim 5 , wherein:
the second epicyclic gear system comprises a rotating ring gear;
the low pressure compressor is coupled to the rotating ring gear.
7. The gas turbine engine of claim 1 , wherein a first speed of the fan and a second speed of the low pressure compressor are independently configured.
8. The gas turbine engine of claim 7 , wherein the first speed and the second speed are both different from a third speed of the low speed spool.