GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT

摘要

A gas turbine engine includes, among other things, a fan section, a core engine, a bypass passage, a bypass ratio defined as the volume of air passing into the bypass passage compared to the volume of air passing into the core engine, the bypass ratio being greater than or equal to 10 at cruise power, and a low fan pressure ratio of less than 1.45 measured across a fan blade alone. A gear arrangement drives the fan section. A compressor section includes both a low pressure compressor and a high pressure compressor. A guide vane includes a forward attachment, the forward attachment positioned aft of a plumbing connection area. A turbine section drives the gear arrangement, and may have a low pressure turbine with a low pressure turbine pressure ratio greater than 5:1, and a two stage high pressure turbine. An overall pressure ratio is provided by the combination of a pressure ratio across the low pressure compressor and a pressure ratio across the high pressure compressor, and greater than 50, measured at sea level and at a static, full-rated takeoff power. The pressure ratio across the high pressure compressor is greater than 7.

主权项

1. A gas turbine engine comprising:
a fan section; a low fan pressure ratio of less than 1.45 measured across a fan blade alone; a core engine, a bypass passage, and a bypass ratio defined as the volume of air passing into the bypass passage compared to the volume of air passing into the core engine, wherein the bypass ratio is greater than 10; a gear arrangement that drives the fan section, the gear arrangement defining a gear reduction ratio of greater than 2.3:1; a compressor section, comprising both a low pressure compressor and a high pressure compressor; a guide vane with a forward attachment, the forward attachment positioned aft of a plumbing connection area; and a turbine section that drives the gear arrangement, the turbine section including a low pressure turbine with an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1, wherein the low pressure turbine pressure ratio is a ratio of a pressure measured prior to the inlet as related to a pressure at the outlet prior to any exhaust nozzle, and wherein the turbine section further includes a two stage high pressure turbine; wherein an overall pressure ratio is:
provided by the combination of a pressure ratio across the low pressure compressor and a pressure ratio across the high pressure compressor; andgreater than 50, measured at sea level and at a static, full-rated takeoff power; and wherein the pressure ratio across the high pressure compressor is greater than 7, measured at sea level and at a static, full-rated takeoff power.