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2. 发明公开

EP4365425A1 GAS TURBINE ENGINE WITH THIRD STREAM 审中-公开
公开(公告)号：EP4365425A1
公开(公告)日：2024-05-08
申请号：EP23207225.6
申请日：2023-10-31
申请人： General Electric Company
发明人： OSTDIEK, David Marion
IPC分类号： F02C3/107 , F02C7/36 , F02K3/02 , F02K3/06 , F02K3/075 , F02K3/115
CPC分类号： F02K3/02 , F02K3/115 , F02C3/107 , F02C7/36 , F05D2260/4031120130101 , F02K3/06 , F02K3/075
摘要： A gas turbine engine defining a centerline and a circumferential direction, the gas turbine engine including: a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the turbomachine defining a working gas flowpath and a fan duct flowpath; a primary fan driven by the turbomachine defining a primary fan tip radius R1 and a primary fan hub radius R2; a secondary fan located downstream of the primary fan and driven by the turbomachine, at least a portion of an airflow from the primary fan configured to bypass the secondary fan, the secondary fan defining a secondary fan tip radius R3 and a secondary fan hub radius R4, wherein the secondary fan is configured to provide a fan duct airflow through the fan duct flowpath during operation to generate a fan duct thrust, wherein the fan duct thrust is equal to %Fn3S of a total engine thrust during operation of the gas turbine engine at a rated speed during standard day operating conditions; wherein a ratio of R1 to R3 equals EFP1−RqRSec.−Fan21−RqRPrim.−Fan21%Fn3s−1; wherein EFP is between 1.5 and 11, wherein RqRPrim.-Fan is a ratio of R1 to R2, and wherein RqRSec.-Fan is a ratio of R3 to R4.

3. 发明公开

EP4219919A1 OVERALL ENGINE EFFICIENCY RATING FOR TURBOMACHINE ENGINES 审中-实审
公开(公告)号：EP4219919A1
公开(公告)日：2023-08-02
申请号：EP22213270.6
申请日：2022-12-13
申请人： General Electric Company , Ge Avio S.r.l.
发明人： PIAZZA, Andrea , CLEMENTS, Jeffrey
IPC分类号： F02C7/06 , F02C7/36 , F02K3/06 , F02C6/20 , F02K3/02
摘要： A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and an overall engine efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include a low-pressure turbine. The gearbox includes an input and an output. The input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, the output of the gearbox is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 3.2-4.0. The overall engine efficiency rating is within a range of 0.57-8.0.

4. 发明公开

EP4212701A1 UNDUCTED THRUST PRODUCING SYSTEM 审中-实审
公开(公告)号：EP4212701A1
公开(公告)日：2023-07-19
申请号：EP23160005.7
申请日：2013-10-23
申请人： General Electric Company
发明人： BREEZE-STRINGFELLOW, Andrew , KHALID, Syed Arif , SMITH, Leroy Harrington Jr.
IPC分类号： F01D5/14 , B64C11/18 , B64C11/46 , F02K3/02 , F02C6/20 , F03D1/06
摘要： An unducted thrust producing system has a rotating element with an axis of rotation and a stationary element. The rotating element includes a plurality of blades each having a blade root proximal to the axis, a blade tip remote from the axis, and a blade span measured between the blade root and the blade tip. The rotating element has a load distribution such that at any location between the blade root and 30% span the value of ΔRCu in the air stream is greater than or equal to 60% of the peak ΔRCu in the air stream.

5. 发明公开

EP4116560A1 BLEED AIR OFFTAKE ASSEMBLY FOR A GAS TURBINE ENGINE 审中-实审
公开(公告)号：EP4116560A1
公开(公告)日：2023-01-11
申请号：EP22183184.5
申请日：2022-07-05
申请人： PRATT & WHITNEY CANADA CORP.
发明人： DUROCHER, Eric
IPC分类号： F02C9/16 , F02K3/02 , F02C6/04
摘要： A gas turbine engine (10A; 10B; 10C) comprising: a duct (30) extending about an axis (C L ), the duct (30) including an outer-duct wall (32) having an interior-duct surface (32i) circumscribing an interior of the duct (30) and an exterior-duct surface (32e) radially outward of the interior-duct surface (32i) relative to the axis (C L ), the outer-duct wall (32) defining an offtake opening (34) extending from the interior-duct surface (32i) to the exterior-duct surface (32e), the offtake opening (34) in fluid communication between an offtake location (L1) inside the duct (30) and outside the duct (30); and a bleed air offtake assembly (40) including: an air line (60) in fluid communication with inside the duct (30) via the offtake opening (34), the air line (60) having a first-line end defining a line inlet (62) proximate to the outer-duct wall (32) and a second-line end spaced from the first-line end; a valve (70) located outside the duct (30) and fluidly connected to the air line (60) via the second-line end, and a conduit (80) having a conduit inlet (82) in fluid communication with inside the air line (60) at a resonance location (L2) between the first-line end and the second-line end upstream of the valve (70), and a conduit outlet (84) in fluid communication with inside the duct (30) at a relief location (L3) spaced from the offtake location (L1).

6. 发明授权

EP2812557B1 GAS TURBINE ENGINE WITH MODULAR CORES AND PROPULSION UNIT 有权转让
公开(公告)号：EP2812557B1
公开(公告)日：2022-12-14
申请号：EP13746242.0
申请日：2013-02-05
发明人： SUCIU, Gabriel L. , DYE, Christopher , STAUBACH, Joseph B.
IPC分类号： F02K3/06 , F02K3/02 , F02K5/00 , F02C7/00 , F02C3/107 , F02C7/04 , F02C7/36

7. 发明公开

EP4098843A1 UNDUCTED THRUST PRODUCING SYSTEM ARCHITECTURE 审中-实审
公开(公告)号：EP4098843A1
公开(公告)日：2022-12-07
申请号：EP22185574.5
申请日：2013-10-23
申请人： General Electric Company
发明人： ZATORSKI, Darek , HAMEL, Jeffrey A. , BREEZE-STRINGFELLOW, Andrew
IPC分类号： F01D5/14 , B64C11/18 , B64C11/46 , F02K3/02 , F02C6/20 , F03D1/06 , B64D33/02 , B64D33/04 , F02K1/46 , F02C7/36
摘要： An unducted thrust producing system has a rotating element with an axis of rotation and a stationary element. The rotating element includes a plurality of blades, and the stationary element has a plurality of vanes configured to impart a change in tangential velocity of the working fluid opposite to that imparted by the rotating element acted upon by the rotating element. The system includes an inlet forward of the rotating element and the stationary element.

8. 发明公开

EP3670865A1 ATTRITABLE ENGINE INTEGRATED WITH VEHICLE 有权转让
公开(公告)号：EP3670865A1
公开(公告)日：2020-06-24
申请号：EP19217135.3
申请日：2019-12-17
申请人： United Technologies Corporation
发明人： BUTCHER, Evan , BOYER, Jesse R. , SHARMA, Om P. , BINEK, Lawrence , DODS, Bryan G. , JAGDALE, Vijay Narayan
IPC分类号： F02C7/20 , F01D25/26 , F01D25/28 , F02K1/80 , F02K1/82 , F02K3/02 , B64D27/14
摘要： A vehicle structure with unitary casing for an attritable gas turbine engine comprising a vehicle structure forming a unitary casing having a casing wall opposite the vehicle structure; a bypass duct formed between the casing wall and the vehicle structure, wherein the unitary casing is configured to receive a core of the attritable gas turbine engine.

9. 发明授权

EP3019721B1 PLATED POLYMER NACELLE 有权转让
公开(公告)号：EP3019721B1
公开(公告)日：2020-02-26
申请号：EP14822381.1
申请日：2014-07-09
申请人： United Technologies Corporation
发明人： ROACH, James T. , WATSON, Charles R. , COOK III, Grant O , SCHWARZ, Frederick M. , BUGAJ, Shari L. , SCHLICHTING, Kevin W.
IPC分类号： F02C7/00 , F02C7/30 , F02K3/02 , F04D29/44 , C25D5/56 , C25D7/00 , C23C18/16 , C23C18/31 , F01D5/28 , F01D5/30 , F01D9/04 , F01D25/00 , F01D25/30 , F01D25/24 , F04D29/02 , F04D29/32 , F04D29/52 , F04D29/54

10. 发明授权

EP2685065B1 Propeller gas turbine engine 有权转让
公开(公告)号：EP2685065B1
公开(公告)日：2018-11-28
申请号：EP13171359.6
申请日：2013-06-11
申请人： Rolls-Royce plc
发明人： Stretton, Richard , Howarth, Nicholas
IPC分类号： F02C3/067 , F02K3/02 , F02K3/06 , F02C7/04 , F02K3/04 , B64D27/00 , F02C7/05
CPC分类号： B64C11/001 , B64D27/00 , B64D2027/005 , F02C3/067 , F02C7/04 , F02C7/05 , F02K3/025 , F02K3/04 , F05D2220/323 , F05D2220/325 , F05D2240/302 , F05D2250/324 , F05D2250/51 , Y02T50/66 , Y02T50/671 , Y02T50/673
摘要： A gas turbine engine (10) having an axial flow direction (X) therethrough in use. The gas turbine engine (10) comprises one or more rotor stages each comprising at least one rotor blade (120) having a root portion (122). The gas turbine engine (10) comprises a shroud (126) located upstream of one or more of the rotor stages relative to the axial flow direction (X). The shroud (126) defines a through passageway (128) extending between an inlet (130) and an outlet (132) which comprises a diffuser region (138). The diffuser region (138) is configured to reduce the axial velocity of air exiting the outlet (132) relative to air entering the diffuser portion (138) in use, wherein the outlet (132) is located such that air exiting the outlet (132) is directed substantially to the root portion (122) only of the rotor blades (120).

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