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 or equal to about 8 at cruise power. A gear arrangement is configured to drive the fan section. A compressor section includes both a first compressor section and a second compressor section. A turbine section is configured to drive the gear arrangement, and may have a low pressure turbine with four stages and a low pressure turbine pressure ratio greater than about 5:1, and a high pressure turbine with two stages. An overall pressure ratio is provided by the combination of a pressure ratio across the first compressor section and a pressure ratio across the second compressor section, and greater than about 40, measured at sea level and at a static, full-rated takeoff power. The pressure ratio across the second compressor section 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 or equal to about 8 at cruise power; a gear arrangement configured to drive the fan section, the gear arrangement defining a gear reduction ratio of greater than about 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 section and a high pressure compressor section; a turbine section configured to drive 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 about 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 section and a pressure ratio across the high pressure compressor section; 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 section is greater than about 7, measured at sea level and at a static, full-rated takeoff power.