GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT

专利名称：GAS TURBINE ENGINE COMPRESSOR

ARRANGEMENT

发明人：Joseph B. Staubach申请号：US133373申请日：20111227

公开号：US20120114479A1公开日：20120510

专利附图：

摘要：A gas turbine engine includes a low pressure compressor section and a highpressure compressor section. A low pressure turbine drives the low pressure compressorsection. A gear arrangement is driven by the low pressure turbine to in turn drive a fan

section. A pressure ratio across the low pressure compressor section is between about 4-8, and a pressure ratio across the high pressure compressor section is between about 8-15. In a separate feature, a compressor case includes a front compressor case portionand a rear compressor case portion, with the rear compressor case portion being axiallyfurther from an inlet case than the front compressor case portion. A support memberextends between the fan section and the front compressor case portion.

申请人：Joseph B. Staubach

地址：Colchester CT US

国籍：US

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