Geared turbofan architecture for improved thrust density
OwnerFrederick M. Schwarz, Daniel Bernard Kupratis +1inventors
InventorsFrederick M. Schwarz, Daniel Bernard Kupratis, Gabriel L. Suciu
Life of this patent
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Abstract
A turbine engine includes a fan, a compressor section having a low pressure compressor section and a high pressure compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The turbine section includes a low pressure turbine section and a high pressure turbine section. The low pressure compressor section, the low pressure turbine section and the fan rotate in a first direction whereas the high pressure compressor section and the high pressure turbine section rotate in a second direction opposite the first direction.
Claims20
A gas turbine engine comprising:
- a fan rotatable about an axis;
- a compressor section having a low pressure compressor section and a high pressure compressor section;
- a combustor in fluid communication with the compressor section;
- a turbine section in fluid communication with the combustor, said turbine section having a low pressure turbine section and a high pressure turbine section;
- and
- a speed change system driven by the turbine section,
- wherein said fan is driven in a first direction by the turbine section through the speed change system,
- wherein said low pressure compressor section and said low pressure turbine section rotate about said axis in the first direction, and
- wherein said high pressure compressor section and said high pressure turbine section rotate about said axis in a second direction opposite said first direction.
A method for increasing a power density of a gas turbine engine comprising the step of:
- rotating a low pressure turbine section and a low pressure compressor section in a first direction;
- rotating a high pressure turbine section and a high pressure compressor section in a second direction opposite the first direction;
- and
- driving a fan through a speed change system in the first direction such that the low pressure turbine section and low pressure compressor section rotate at a speed greater than the fan.
Dependencies are inferred from the claim text.