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公开(公告)号：US10066504B2
公开(公告)日：2018-09-04
申请号：US14774407
申请日：2014-03-13
摘要： A turbofan engine (20; 300; 400) comprises a fan (28), a fan drive gear system (60), a fan shaft (120) coupling the fan drive gear system to the fan, a low spool, an intermediate spool, and a core spool. The low spool engages at least three main bearings of which at least two are non-thrust bearings and at least one is a thrust bearing. The fan shaft engages at least two bearings (148, 150). The core spool engages at least two bearings (250, 260). The intermediate spool engages at least two of said bearings (220, 200, 230; 220, 200, 230-2; 200, 220, 230-3).
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公开(公告)号：US20180245541A1
公开(公告)日：2018-08-30
申请号：US15962039
申请日：2018-04-25
IPC分类号： F02K3/06 , F02C7/36 , F02K3/072 , F01D9/04 , F02C9/18 , F01D5/06 , F01D9/02 , F02C3/04 , F02K1/78 , F04D27/00 , F04D29/32 , F02C3/107 , F01D25/16 , F02C7/06 , F01D5/02
CPC分类号： F02K3/06 , F01D5/02 , F01D5/06 , F01D9/02 , F01D9/041 , F01D25/164 , F02C3/04 , F02C3/107 , F02C7/06 , F02C7/36 , F02C9/18 , F02K1/78 , F02K3/072 , F04D27/009 , F04D29/325 , F05D2220/32 , F05D2220/323 , F05D2220/36 , F05D2240/24 , F05D2240/35 , F05D2240/40 , F05D2250/30 , F05D2260/40311 , F05D2260/96 , Y02T50/671 , Y02T50/673
摘要： A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.
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公开(公告)号：US10060353B2
公开(公告)日：2018-08-28
申请号：US14826871
申请日：2015-08-14
CPC分类号： F02C7/185 , F01D25/12 , F02C7/141 , F02C7/32 , F05D2220/32 , F05D2240/91 , F05D2250/42 , F05D2260/213 , F05D2260/232 , F05D2260/30 , F05D2260/941 , F28F9/002 , F28F2265/26 , Y02T50/675
摘要： A heat exchanger (HEX) for cooling air in a gas turbine engine is provided. The HEX may comprise an intake manifold in fluid communication with a compressor section and configured to receive air from the compressor section, an outtake manifold in fluid communication with the intake manifold via a tube, and a cooling air flow path defined by at least one of an outer surface of the tube, an outer surface of the intake manifold, and an outer surface of the outtake manifold, wherein the cooling air flow path is orthogonal to said tube. The air from the intake manifold may travel through the tube to the outtake manifold and from the outtake manifold to a portion of the gas turbine engine.
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公开(公告)号：US20180223736A1
公开(公告)日：2018-08-09
申请号：US15424927
申请日：2017-02-06
CPC分类号： F02C7/185 , F01D25/12 , F02C3/107 , F02C6/08 , F02C7/18 , F05D2260/213 , Y02T50/676
摘要： A gas turbine engine comprises a compressor section and a turbine section, the compressor section having a last compressor stage. High pressure cooling air is tapped from a location downstream of the last compressor stage and passed through a heat exchanger. Lower pressure air passes across the heat exchanger to cool the high pressure cooling air. A housing surrounds the compressor section and the turbine section and there being a space radially outwardly of the housing, and a mixing chamber received in the space radially outwardly of the housing, the mixing chamber receiving the high pressure cooling air downstream of the heat exchanger, and further receiving air at a temperature higher than a temperature of the high pressure cooling air downstream of the heat exchanger. Mixed air from the mixing chamber is returned into the housing and utilized to cool at least the turbine section.
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公开(公告)号：US20180211336A1
公开(公告)日：2018-07-26
申请号：US15412293
申请日：2017-01-23
CPC分类号： G06Q50/04 , G01M5/0016 , G01M15/14 , G05B23/0283 , G06Q10/06315 , G06Q10/0875 , Y02P90/30
摘要： A method of determining a use for substantially the same gas turbine engine components and comprises the steps of receiving manufacturing information about a plurality of gas turbine engine components; classifying each of the plurality of gas turbine engine components into at least two categories, with a first category being components closer to a specification than a second category; and recommending a suggested future use for the first category on aircraft that will operate in more challenging flight conditions and for the second category on aircraft that will operate in less challenging flight conditions. A system is also disclosed.
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公开(公告)号：US20180149036A1
公开(公告)日：2018-05-31
申请号：US15881240
申请日：2018-01-26
发明人： Michael E. McCune , Jason Husband , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann
CPC分类号： F01D15/12 , F01D5/06 , F01D9/041 , F02C3/107 , F02C7/20 , F02C7/36 , F02K3/06 , F04D19/002 , F04D25/045 , F04D29/053 , F04D29/325 , F05D2220/32 , F05D2220/323 , F05D2240/60 , F05D2260/4031 , F05D2260/40311 , F05D2300/501 , Y02T50/671
摘要： A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with some flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is relatively high.
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公开(公告)号：US20180128168A1
公开(公告)日：2018-05-10
申请号：US15843012
申请日：2017-12-15
摘要： A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool and the fan drive turbine configured to rotate in the same first direction. The intermediate speed spool rotates in an opposed, second direction.
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公开(公告)号：US20170370220A1
公开(公告)日：2017-12-28
申请号：US15191885
申请日：2016-06-24
CPC分类号： F01D5/005 , B23P6/002 , F01D5/12 , F01D9/02 , F01D21/003 , F01D21/14 , F04D29/324 , F04D29/542 , F05D2230/72 , F05D2230/80 , F05D2260/81 , F05D2260/82 , F05D2260/821 , F05D2270/09 , G01M15/14 , Y02T50/673
摘要： A method of developing a suggested blend repair to an airfoil includes the steps of: (a) storing history with regard to a particular airfoil in a particular engine; (b) taking information with regard to new damage to the particular airfoil; (c) reaching an initial blend recommendation based upon step (b); (d) assessing whether the initial blend recommendation of step (c) would be appropriate to repair the new damage based upon a consideration of steps (a)-(c); and (e) reporting a final blend recommendation. An airfoil repair recommendation system is also disclosed.
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39.发明授权公开(公告)号：US09835052B2
公开(公告)日：2017-12-05
申请号：US15478671
申请日：2017-04-04
发明人： Frederick M. Schwarz , Gabriel L. Suciu , William K. Ackermann , Daniel Bernard Kupratis , Michael E. McCune
IPC分类号： F02C7/36 , F01D25/16 , F04D29/32 , F04D25/04 , F04D19/02 , F01D5/06 , F01D9/04 , F02C3/107 , F01D15/12 , F02C3/04 , F02K3/06
CPC分类号： F01D25/164 , F01D5/06 , F01D9/041 , F01D15/12 , F02C3/04 , F02C3/107 , F02C7/06 , F02C7/20 , F02C7/36 , F02K3/06 , F04D19/02 , F04D25/028 , F04D25/045 , F04D29/056 , F04D29/325 , F04D29/668 , F05D2220/32 , F05D2240/60 , F05D2260/40311
摘要： A gas turbine engine according to an example of the present disclosure includes, among other things, a fan, a compressor section, and a turbine section including a fan drive turbine and a second turbine. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. A mid-turbine frame is positioned intermediate the fan drive turbine and the second turbine, and can include a bearing support. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.
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40.发明申请公开(公告)号：US20170298767A1
公开(公告)日：2017-10-19
申请号：US15478706
申请日：2017-04-04
发明人： Frederick M. Schwarz , Gabriel L. Suciu , William K. Ackermann , Daniel Bernard Kupratis , Michael E. McCune
IPC分类号： F01D25/16 , F01D9/04 , F04D19/02 , F01D5/06 , F04D29/32 , F04D27/00 , F04D25/04 , F04D25/02 , F02C3/04 , F02K3/06
CPC分类号： F01D25/164 , F01D5/06 , F01D9/041 , F01D15/12 , F01D25/162 , F02C3/04 , F02C3/107 , F02C7/06 , F02C7/20 , F02C7/36 , F02K3/06 , F04D19/02 , F04D25/028 , F04D25/045 , F04D27/009 , F04D29/056 , F04D29/325 , F04D29/668 , F05D2220/32 , F05D2240/60 , F05D2260/40311
摘要： A gas turbine engine according to an example of the present disclosure includes, among other things, a turbine section including a fan drive turbine and a second turbine. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. A mid-turbine frame is positioned intermediate the fan drive turbine and the second turbine, and can include a bearing support. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.
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