Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
  • F01D25/243—Flange connections; Bolting arrangements
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
  • F01D25/26—Double casings; Measures against temperature strain in casings
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2240/00—Components
  • F05D2240/10—Stators
  • F05D2240/14—Casings or housings protecting or supporting assemblies within
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2300/00—Materials; Properties thereof
  • F05D2300/70—Treatment or modification of materials
  • F05D2300/702—Reinforcement

Definitions

• the present disclosure relates to a gas turbine engine and, more particularly, to a case structure therefor.
• Gas turbine engines such as those that power modern commercial and military aircraft, generally include a compressor section to pressurize an airflow, a combustor section for burning a hydrocarbon fuel in the presence of the pressurized air, and a turbine section to extract energy from the resultant combustion gases.
• An engine case structure formed of multiple cases or modules to facilitate assembly surround these sections. Each cases typically abuts another case at a flange. The engine cases are subject to a harsh environment as the products of combustion at high temperature pass therethrough.
• a case for a gas turbine engine includes an integrated High Pressure Compressor Diffuser case operable to contain a combustor section and a portion of a compressor section.
• the integrated HPC Diffuser case is a housing with a reinforced area.
• the reinforced area defines an increased thickness.
• the integrated HPC Diffuser case includes a HPC flange to provide a bolted connection with a HPC case.
• the integrated HPC Diffuser case includes a HPT flange to provide a bolted connection with a HPT case.
• the integrated HPC Diffuser case includes a HPC flange to provide a bolted connection with a HPC case and a HPT flange to provide a bolted connection with a HPT case.
• no flange is located between said HPC flange and said HPT flange.
• a boss arrangement is located between said HPC flange and said HPT flange.
• the portion of said compressor section includes two stages.
• the portion of said compressor section includes two stages of an eight stage High Pressure Compressor.
• a case assembly of a gas turbine engine includes a fan case, an intermediate case boltable to said fan case, a High Pressure Compressor case boltable to said intermediate case, an integrated High Pressure Compressor Diffuser case boltable to said High Pressure Compressor case, a High Pressure Turbine case boltable to said integrated High Pressure Compressor Diffuser case, a Mid Turbine Frame case boltable to said High Pressure Turbine case, a Low Pressure Turbine case boltable to said Mid Turbine Frame case and a Turbine Exhaust case boltable to said Low Pressure Turbine case.
• Diffuser case includes a housing with a reinforced area.
• the reinforced area defines an increased thickness.
• the integrated HPC Diffuser case includes a HPC flange to provide a bolted connection with a HPC case and a HPT flange to provide a bolted connection with a HPT case.
• a boss arrangement is located between said HPC flange and said HPT flange.
• the integrated HPC Diffuser case is operable to contain a combustor section and a portion of a High Pressure Compressor.
• the portion of said High Pressure Compressor includes two stages. In the alternative or additionally thereto, in the foregoing embodiment the portion of said High Pressure Compressor includes two stages of an eight stage High Pressure Compressor.
• Pressure Compressor case is a split case.
• Figure 1 is a schematic cross-section of a gas turbine engine
• FIG. 1 is a schematic view of a gas turbine engine case structure
• Figure 3 is an expanded perspective view of an integrated HPC Diffuser case
• Figure 4 is an expanded perspective view of a RELATED ART HPC rear case bolted to a Diffuser case
• Figure 5 is an expanded unrolled view of the integrated HPC Diffuser case illustrating a boss arrangement.
• FIG. 1 schematically illustrates a gas turbine engine 20.
• the gas turbine engine 20 is disclosed herein as a two-spool turbo fan that generally incorporates a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28.
• Alternative engines might include an augmentor section (not shown) among other systems or features.
• the fan section 22 drives air along a bypass flowpath while the compressor section 24 drives air along a core flowpath for compression and communication into the combustor section 26 then expansion through the turbine section 28.
• turbofan in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use with turbofans as the teachings may be applied to other types of turbine engines such as a turbojets, turboshafts, and three-spool (plus fan) turbofans wherein an intermediate spool includes an intermediate pressure compressor ("IPC") between a Low Pressure Compressor (“LPC”) and a High Pressure Compressor (“HPC”), and an intermediate pressure turbine (“ ⁇ ”) between the high pressure turbine (“HPT”) and the Low pressure Turbine (“LPT”).
• IPC intermediate pressure compressor
• LPC Low Pressure Compressor
• HPC High Pressure Compressor
• ⁇ intermediate pressure turbine
• the engine 20 generally includes a low spool 30 and a high spool 32 mounted for rotation about an engine central longitudinal axis A relative to an engine case assembly 36 via several bearing structures 38.
• the low spool 30 generally includes an inner shaft 40 that interconnects a fan 42, a low pressure compressor 44 ("LPC") and a low pressure turbine 46 ("LPT").
• the inner shaft 40 drives the fan 42 directly or through a geared architecture 48 to drive the fan 42 at a lower speed than the low spool 30.
• An exemplary reduction transmission is an epicyclic transmission, namely a planetary or star gear system.
• the high spool 32 includes an outer shaft 50 that interconnects a high pressure compressor 52 (“HPC”) and high pressure turbine 54 (“HPT").
• a combustor 56 is arranged between the high pressure compressor 52 and the high pressure turbine 54.
• the inner shaft 40 and the outer shaft 50 are concentric and rotate about the engine central longitudinal axis A which is collinear with their longitudinal axes.
• the gas turbine engine 20 is a high-bypass geared aircraft engine.
• the gas turbine engine 20 bypass ratio is greater than about six (6:1).
• the geared architecture 48 can include an epicyclic gear train, such as a planetary gear system or other gear system.
• the example epicyclic gear train has a gear reduction ratio of greater than about 2.3, and in another example is greater than about 2.5: 1.
• the geared turbofan enables operation of the low spool 30 at higher speeds which can increase the operational efficiency of the low pressure compressor 44 and low pressure turbine 46 and render increased pressure in a fewer number of stages.
• a pressure ratio associated with the low pressure turbine 46 is pressure measured prior to the inlet of the low pressure turbine 46 as related to the pressure at the outlet of the low pressure turbine 46 prior to an exhaust nozzle of the gas turbine engine 20.
• the bypass ratio of the gas turbine engine 20 is greater than about ten (10:1)
• the fan diameter is significantly larger than that of the low pressure compressor 44
• the low pressure turbine 46 has a pressure ratio that is greater than about five (5:1). It should be understood, however, that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present disclosure is applicable to other gas turbine engines including direct drive turbofans.
• a significant amount of thrust is provided by the bypass flow path B due to the high bypass ratio.
• the fan section 22 of the gas turbine engine 20 is designed for a particular flight condition - typically cruise at about 0.8 Mach and about 35,000 feet. This flight condition, with the gas turbine engine 20 at its best fuel consumption, is also known as bucket cruise Thrust Specific Fuel Consumption (TSFC). TSFC is an industry standard parameter of fuel consumption per unit of thrust.
• Fan Pressure Ratio is the pressure ratio across a blade of the fan section 22 without the use of a Fan Exit Guide Vane system.
• the low Fan Pressure Ratio according to one non-limiting embodiment of the example gas turbine engine 20 is less than 1.45.
• Low Corrected Fan Tip Speed is the actual fan tip speed divided by an industry standard temperature correction of ("T" / 518.7 0'5 ) in which "T" represents the ambient temperature in degrees Rankine.
• the Low Corrected Fan Tip Speed according to one non-limiting embodiment of the example gas turbine engine 20 is less than about 1150 fps (351 m/s).
• the engine case assembly 36 generally includes a multiple of cases or modules to include a fan case 60, an intermediate case 62, a HPC split case 64, an integrated High Pressure Compressor (HPC) diffuser case 66, a High Pressure Turbine (HPT) case 68, a mid turbine frame (MTF) case 70, a Low Pressure Turbine (LPT) case 72, and a Turbine Exhaust case (TEC) 74.
• HPC split case 64 an integrated High Pressure Compressor (HPC) diffuser case 66
• HPT High Pressure Turbine
• MTF mid turbine frame
• LPT Low Pressure Turbine
• TEC Turbine Exhaust case
• the fan case 60 is bolted to the intermediate case 62 which is bolted to the HPC split case 64 which is bolted to the integrated HPC diffuser case 66 which is bolted to the HPT case 68 which is bolted to the mid turbine frame (MTF) case 70 which is bolted to the LPT case 72 which is bolted to the turbine exhaust case (TEC) 74 each at a respective flange.
• the intermediate case 62 which is bolted to the HPC split case 64 which is bolted to the integrated HPC diffuser case 66 which is bolted to the HPT case 68 which is bolted to the mid turbine frame (MTF) case 70 which is bolted to the LPT case 72 which is bolted to the turbine exhaust case (TEC) 74 each at a respective flange.
• MTF mid turbine frame
• TEC turbine exhaust case
• the integrated HPC diffuser case 66 is mounted between the split HPC case 64 and the HPT case 68 to surround the last two stages of an eight (8) stage HPC 52 and the combustor 56. That is, the integrated HPC diffuser case 66 contains the combustor 56 and a portion of the HPC 52.
• the integrated HPC diffuser case 66 generally includes a housing 76 with a reinforced area 78.
• the reinforced area 78 is a selectively thickened area that provides strength in desired locations as compared with the separate structural arrangement provided by the heretofore utilized separate HPC rear case H and diffuser case D with a flange F therebetween ( Figure 4; RELATED ART).
• the integrated HPC diffuser case 66 includes a HPC flange 80 to provide a bolted connection with the HPC split case 64 and a HPT flange 82 to provide a bolted connection with the HPT case 68.
• the integrated HPC diffuser case 66 provides a shorter overall engine length through elimination of the flange F (Figure 4; RELATED ART) which facilitates a more efficient and compact boss arrangement 84 ( Figure 5).
• a row fuel injector bosses 86 are arranged generally along the middle of the integrated HPC diffuser case 66 between the flanges 80, 82.
• Environmental Control System (ECS) bosses 88 are telescoped at least partially into the row fuel injector bosses 86. It should be appreciated that various bosses may additionally or alternatively be provided.

Landscapes

• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)

Applications Claiming Priority (2)

Publications (2)

Family

ID=50389056

Family Applications (1)

Country Status (3)

Families Citing this family (6)

Family Cites Families (9)

• 2013
  • 2013-09-30 EP EP13841258.0A patent/EP2900940A4/de not_active Withdrawn
  • 2013-09-30 US US14/432,440 patent/US20150240662A1/en not_active Abandoned
  • 2013-09-30 WO PCT/US2013/062662 patent/WO2014052967A1/en not_active Ceased

Also Published As

Similar Documents

Legal Events