GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT

摘要

A gas turbine engine includes, among other things, a fan section, 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, the bypass ratio being greater than 8 at cruise power. A gear arrangement drives the fan section. A guide vane includes a forward attachment, the forward attachment positioned aft of a plumbing connection area. A compressor section includes both a first compressor and a second compressor. A lubrication system and a compressed air system are in fluid communication with the gear arrangement. A turbine section drives the gear arrangement, and includes a low pressure turbine. An overall pressure ratio is provided by the combination of a pressure ratio across the first compressor and a pressure ratio across the second compressor, and greater than about 50, measured at sea level and at a static, full-rated takeoff power. The pressure ratio across the second compressor is greater than about 7.

主权项

1. A gas turbine engine comprising:
a fan section; 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 8 at cruise power; a gear arrangement that drives the fan section, the gear arrangement defining a gear reduction ratio of greater than 2.3:1; a lubrication system and a compressed air system in fluid communication with the gear arrangement; a compressor section, comprising both a low pressure compressor and a high pressure compressor; a guide vane comprising 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; 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 about 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 about 7, measured at sea level and at a static, full-rated takeoff power.