Gas turbine engine compressor arrangement

Abstract

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.

We claim: 
     
         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; and 
 greater 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.   
     
     
         2 . The gas turbine engine of  claim 1 , wherein the plumbing connection area is removable with the gear arrangement. 
     
     
         3 . The gas turbine engine of  claim 1 , further comprising a low fan pressure ratio of less than about 1.45 measured across a fan blade alone, and wherein the bypass ratio is greater than 10. 
     
     
         4 . The gas turbine engine of  claim 3 , wherein the turbine section further comprises a two stage high pressure turbine. 
     
     
         5 . The gas turbine engine of  claim 4 , wherein the low pressure turbine is a four stage turbine. 
     
     
         6 . The gas turbine engine of  claim 5 , wherein the low pressure compressor is a three stage compressor. 
     
     
         7 . The gas turbine engine of  claim 6 , wherein the high pressure compressor is a nine stage compressor. 
     
     
         8 . The gas turbine engine of  claim 5 , wherein the low fan pressure ratio is less than 1.45. 
     
     
         9 . The gas turbine engine of  claim 8 , wherein the gear arrangement is a planetary gear system with a sun gear, a ring gear, and a plurality of orbiting planet gears arranged circumferentially about the sun gear and intermeshing with the sun gear and the ring gear. 
     
     
         10 . The gas turbine engine of  claim 9 , wherein the pressure ratio across the low pressure compressor is less than 6, measured at sea level and at a static, full-rated takeoff power. 
     
     
         11 . The gas turbine engine of  claim 5 , wherein the plumbing connection area is removable with the gear arrangement. 
     
     
         12 . The gas turbine engine of  claim 1 , further comprising a low fan pressure ratio of less than about 1.35 measured across a fan blade alone, and wherein the bypass ratio is greater than 10, the turbine section includes a two stage high pressure turbine, and the pressure ratio across the low pressure compressor is less than about 6, measured at sea level and at a static, full-rated takeoff power. 
     
     
         13 . A gas turbine engine comprising:
 a fan section;   a low fan pressure ratio of less than about 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 about 8 at cruise power;   a gear arrangement that drives the fan section, the gear arrangement having a gear system with a sun gear, a ring gear, and a plurality of intermediate gears arranged circumferentially about the sun gear and intermeshing with the sun gear and the ring gear;   a compressor section, comprising both a first compressor section and a second compressor section;   a plumbing connection area that provides access to at least one of compressed air from a compressed air system, or oil from a lubrication system;   a guide vane having a forward attachment, the forward attachment positioned aft of the plumbing connection area; and   a turbine section that drives the gear arrangement, the turbine section including a four stage first turbine;   wherein 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; and 
   wherein the pressure ratio across the second compressor section is greater than about 7, measured at sea level and at a static, full-rated takeoff power.   
     
     
         14 . The gas turbine engine of  claim 13 , wherein the turbine section further has a two stage second turbine, the second turbine upstream of the first turbine. 
     
     
         15 . The gas turbine engine of  claim 14 , wherein:
 the bypass ratio is greater than 10; and   the first turbine comprises an inlet, an outlet, and a pressure ratio greater than 5:1, wherein the 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.   
     
     
         16 . The gas turbine engine of  claim 15 , wherein the lubrication system and the compressed air system are in fluid communication with the gear arrangement. 
     
     
         17 . The gas turbine engine of  claim 16 , wherein the plumbing connection area provides access to the both the compressed air system and the lubrication system. 
     
     
         18 . The gas turbine engine of  claim 17 , wherein:
 the gear arrangement is a planetary gear system; and   the overall pressure ratio is greater than 50, measured at sea level and at a static, full-rated takeoff power.   
     
     
         19 . A gas turbine engine comprising:
 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 that drives a 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 and a high pressure compressor;   a plumbing connection area that provides access to at least one of compressed air from the compressed air system, or oil from the lubrication system;   a guide vane having a forward attachment, the forward attachment positioned aft of the plumbing connection area; and   a turbine section that drives the gear arrangement, the turbine section including a four stage low pressure turbine, 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 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 about 40, 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.   
     
     
         20 . The gas turbine engine of  claim 19 , further comprising a low fan pressure ratio of less than about 1.45 measured across a fan blade alone, and wherein the bypass ratio is greater than 10. 
     
     
         21 . The gas turbine engine of  claim 20 , wherein the low fan pressure ratio is less than 1.45. 
     
     
         22 . The gas turbine engine of  claim 21 , wherein the pressure ratio across the low pressure compressor is less than 6, measured at sea level and at a static, full-rated takeoff power. 
     
     
         23 . The gas turbine engine of  claim 22 , wherein:
 the gear arrangement is a planetary gear system with a sun gear, a ring gear, and a plurality of orbiting planet gears arranged circumferentially about the sun gear and intermeshing with the sun gear and the ring gear; and   the turbine section includes a two stage high pressure turbine.   
     
     
         24 . The gas turbine engine of  claim 23 , wherein the fan pressure ratio is less than 1.35, and the gear arrangement is positioned between the fan section on one side and the low pressure compressor on another side. 
     
     
         25 . 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 about 8 at cruise power;   a gear arrangement that drives the fan section;   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 plumbing connection area;   a guide vane having a forward attachment, the forward attachment positioned aft of the plumbing connection area; and   a turbine section that drives the gear arrangement, the turbine section having 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; and 
 greater than about 40, 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.   
     
     
         26 . The gas turbine engine of  claim 25 , further comprising a low fan pressure ratio of less than about 1.45 measured across a fan blade alone, and wherein the bypass ratio is greater than 10. 
     
     
         27 . The gas turbine engine of  claim 26 , wherein the low fan pressure ratio is less than 1.45. 
     
     
         28 . The gas turbine engine of  claim 27 , wherein the overall pressure ratio is greater than 50, measured at sea level and at a static, full-rated takeoff power. 
     
     
         29 . The gas turbine engine of  claim 28 , wherein the low fan pressure ratio is less than 1.35, and the low pressure turbine is a four stage turbine. 
     
     
         30 . The gas turbine engine of  claim 29 , wherein the gear arrangement is a planetary gear system with a sun gear, a ring gear, and a plurality of orbiting planet gears arranged circumferentially about the sun gear and intermeshing with the sun gear and the ring gear.