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公开(公告)号：EP3339606A1
公开(公告)日：2018-06-27
申请号：EP17191309.8
申请日：2017-09-15
发明人： MORGAN, Keith , PELUSO, Robert , PLANTE, Ghislain , GEKHT, Eugene , DUROCHER, Eric , DUBREUIL, Jean
IPC分类号： F02C3/14
CPC分类号： F02C7/32 , F02C3/145 , F02C6/206 , Y02T50/671
摘要： A gas turbine engine (10) has a first spool (20) having a low pressure compressor section (22) disposed forward of an air inlet (11) along a direction of travel of the engine (10), and a low pressure turbine section (21) disposed forward of the low pressure compressor section (22) and drivingly engaged thereto. A second spool (40) has a high pressure compressor section (42) disposed forward of the low pressure compressor section (22), and a high pressure turbine section (41) disposed forward of the high pressure compressor section (42) and drivingly engaged thereto. The high pressure turbine section (41) is disposed aft of the low pressure turbine section (21). An output drive shaft (24) drivingly engages the low pressure turbine section (21) and extends forwardly therefrom to drive a rotatable load (16). A method of operating a gas turbine engine (10) is also discussed.
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公开(公告)号：EP3957839A1
公开(公告)日：2022-02-23
申请号：EP21195355.9
申请日：2017-09-15
发明人： MORGAN, Keith , PELUSO, Robert , PLANTE, Ghislain , GEKHT, Eugene , DUROCHER, Eric , DUBREUIL, Jean
摘要： A gas turbine engine (10) has a first spool (20) having a low pressure compressor section (22) disposed forward of an air inlet (11) along a direction of travel of the engine (10), and a low pressure turbine section (21) disposed forward of the low pressure compressor section (22) and drivingly engaged thereto. A second spool (40) has a high pressure compressor section (42) disposed forward of the low pressure compressor section (22), and a high pressure turbine section (41) disposed forward of the high pressure compressor section (42) and drivingly engaged thereto. The high pressure turbine section (41) is disposed aft of the low pressure turbine section (21). An output drive shaft (24) drivingly engages the low pressure turbine section (21) and extends forwardly therefrom to drive a rotatable load (16). A method of operating a gas turbine engine (10) is also discussed.
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公开(公告)号：EP3623600A1
公开(公告)日：2020-03-18
申请号：EP19196822.1
申请日：2019-09-11
摘要： An aircraft engine (10) has a high pressure spool (40) including a high pressure turbine (41) drivingly connected to a high pressure compressor (42). A low pressure spool (20) including a low pressure compressor (22) is fluidly connected to the high pressure compressor (42). A low pressure turbine (21) is drivingly connected to the low pressure compressor (22) to drive the low pressure compressor. A load (16) is drivingly connected to the low pressure turbine (21), the load consisting of one of a propeller and a helicopter rotor. A method of creating classes of an aircraft engine from an engine platform (30) is disclosed.
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