Abstract:
A gas turbine engine (20) typically includes a fan section (22), a compressor section (24), a combustor section (26) and a turbine section (28). A speed reduction device such as an epicyclical gear assembly (48) may be utilized to drive the fan section (22) such that the fan section (22) may rotate at a speed different than the turbine section (28) so as to increase the overall propulsive efficiency of the engine (20). In such engine architectures, a shaft (40) driven by a fan drive turbine section (46) provides an input to the epicyclical gear assembly (48) that drives the fan section (22) at a speed different than the fan drive turbine section (46) such that both the fan drive turbine section (46) and the fan section (22) can rotate at closer to optimal speeds providing increased performance attributes and performance.
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.
Abstract:
A seal for use between a first duct and a second duct and, the ducts having relative motion therebetween, includes a first plurality of fingers for attachment to the first duct to be disposed about one of the first duct and the second duct, a seal land attaching to about an other of the first duct and the second duct, and a seal attaching to the seal land and in contact with the plurality of fingers wherein one of the plurality of fingers and the seal is metallic and an other of the seal land or the plurality of fingers is non-metallic.