US2017122220A1PendingUtilityA1

Gas turbine engine compressor arrangement

59
Assignee: UNITED TECHNOLOGIES CORPPriority: Sep 21, 2007Filed: Jan 20, 2017Published: May 4, 2017
Est. expirySep 21, 2027(~1.2 yrs left)· nominal 20-yr term from priority
Inventors:Karl L. HaselJoseph B. StaubachBrian D. MerryGabriel L. SuciuChristopher M. Dye
F02C 7/36F01D 9/02F02C 3/06F05D 2260/40311F02C 7/06F02C 9/18F05D 2220/323F02K 3/06F01D 21/003F05D 2240/35F01D 5/06F01D 25/24F02K 3/025F02C 3/107F02C 3/04F05D 2260/4031F05D 2220/32
59
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Claims

Abstract

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.

Claims

exact text as granted — not AI-modified
We claim: 
     
         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; and 
 greater 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.   
     
     
         2 . The gas turbine engine of  claim 1 , wherein the plumbing connection area provides access to at least one of compressed air from a compressed air system, or oil from a lubrication system. 
     
     
         3 . The gas turbine engine as set forth in  claim 2 , wherein the fan section has a low corrected fan tip speed of less than 1150 ft/second. 
     
     
         4 . The gas turbine engine of  claim 3 , wherein the gear arrangement is positioned between the fan section on one side and the low pressure compressor on another side. 
     
     
         5 . The gas turbine engine of  claim 4 , wherein the low fan pressure ratio is less than 1.35. 
     
     
         6 . The gas turbine engine of  claim 5 , wherein the low pressure turbine is a four stage turbine. 
     
     
         7 . The gas turbine engine of  claim 5 , wherein the low pressure compressor is a three stage compressor. 
     
     
         8 . The gas turbine engine of  claim 7 , wherein the high pressure compressor is a nine stage compressor. 
     
     
         9 . The gas turbine engine of  claim 7 , wherein the overall pressure ratio is less than or equal to 70. 
     
     
         10 . The gas turbine engine of  claim 1 , wherein the high pressure compressor is a nine stage compressor, and the low pressure compressor is a three stage compressor. 
     
     
         11 . The gas turbine engine of  claim 1 , wherein the low pressure turbine is a four stage turbine. 
     
     
         12 . The gas turbine engine of  claim 11 , wherein the low fan pressure ratio is less than 1.35. 
     
     
         13 . The gas turbine engine of  claim 12 , wherein the plumbing connection area provides access to both compressed air from a compressed air system, and oil from a lubrication system. 
     
     
         14 . The gas turbine engine of  claim 13 , 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. 
     
     
         15 . 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 comprising a forward attachment, the forward attachment positioned aft of a plumbing connection area;   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; and 
 greater 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.   
     
     
         16 . The gas turbine engine of  claim 15 , wherein the plumbing connection area provides access to at least one of compressed air from a compressed air system, or oil from a lubrication system. 
     
     
         17 . The gas turbine engine of  claim 16 , wherein the fan section and the low pressure compressor are rotatable in a common direction. 
     
     
         18 . The gas turbine engine of  claim 17 , wherein the low pressure turbine is a four stage turbine. 
     
     
         19 . The gas turbine engine as set forth in  claim 16 , wherein the fan section has a low corrected fan tip speed of less than 1150 ft/second. 
     
     
         20 . The gas turbine engine of  claim 19 , wherein the high pressure compressor is a nine stage compressor, and the low pressure compressor is a three stage compressor. 
     
     
         21 . The gas turbine engine of  claim 19 , wherein the low pressure compressor is a three stage compressor. 
     
     
         22 . The gas turbine engine of  claim 21 , wherein the low pressure turbine is a four stage turbine. 
     
     
         23 . The gas turbine engine of  claim 19 , wherein the high pressure compressor is a nine stage compressor. 
     
     
         24 . The gas turbine engine as set forth in  claim 16 , wherein the fan section has a low corrected fan tip speed of less than 1150 ft/second. 
     
     
         25 . The gas turbine engine of  claim 24 , wherein the low pressure turbine is a four stage turbine. 
     
     
         26 . The gas turbine engine of  claim 25 , wherein the low fan pressure ratio is less than 1.35, measured across a fan blade alone, when the engine is at cruise power. 
     
     
         27 . The gas turbine engine of  claim 25 , wherein the gear arrangement is positioned between the fan section on one side and the low pressure compressor on another side. 
     
     
         28 . The gas turbine engine of  claim 25 , wherein the low pressure compressor is a three stage compressor. 
     
     
         29 . The gas turbine engine of  claim 25 , wherein the plumbing connection area is removable with the gear arrangement. 
     
     
         30 . The gas turbine engine of  claim 25 , wherein the overall pressure ratio is less than or equal to 70.

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