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公开(公告)号：US20200063568A1
公开(公告)日：2020-02-27
申请号：US16283287
申请日：2019-02-22
Applicant: ROLLS-ROYCE plc
Inventor： Martin N. GOODHAND , Ian M. BUNCE
IPC: F01D5/14
Abstract: A turbomachine (105) configured to compress supercritical carbon dioxide is shown. The turbomachine comprises, in fluid flow series, an inlet (201), an inducerless radial impeller (202) having a plurality of backswept blades (211,212) each of which have a blade exit angle (χ2) of from −50 to −70 degrees, and a fully vaneless diffuser (203).
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公开(公告)号：US20200157945A1
公开(公告)日：2020-05-21
申请号：US16672648
申请日：2019-11-04
Applicant: ROLLS-ROYCE plc
Inventor： Martin N. GOODHAND
Abstract: A boundary layer ingestion fan system for location aft of the fuselage of an aircraft is shown. It comprises a nacelle defining a duct, and a fan located within the duct. The fan comprises a hub arranged to rotate around a rotational axis and a plurality of blades attached to the hub, each of which has a span from a root at the hub defining a 0 percent span position (rhub) to a tip defining a 100 percent span position (rtip) and a plurality of span positions therebetween (r∈[rhub, rtip]). The hub has a negative hade angle (γ) with respect to the rotational axis at an axial o position coincident with the leading edge of the blades.
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公开(公告)号：US20200063567A1
公开(公告)日：2020-02-27
申请号：US16283043
申请日：2019-02-22
Applicant: ROLLS-ROYCE plc
Inventor： Martin N. GOODHAND , Ian M. BUNCE
IPC: F01D5/14
Abstract: A turbomachine (105) configured to compress supercritical carbon dioxide is shown. The turbomachine comprises, in fluid flow series, an inlet (201), an inducerless radial impeller (202) having a plurality of blades, and a fully vaneless diffuser (203). The inlet is radially flared to induce a radial component in flow prior to an entry to the impeller.
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公开(公告)号：US20220112817A1
公开(公告)日：2022-04-14
申请号：US17495418
申请日：2021-10-06
Applicant: ROLLS-ROYCE PLC
Inventor： Stephen J. BRADBROOK , Martin N. GOODHAND , Paul M. HIELD , Andrew PARSLEY , Natalie C. WONG , Robert J. CORIN , Thomas S. BINNINGTON
Abstract: A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, and an exhaust module. The fan assembly includes a plurality of fan blades defining a fan diameter. The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and the heat exchanger module including a plurality of heat transfer elements for transfer of heat from a first fluid contained within the heat transfer elements to an airflow passing over a surface of the heat transfer elements prior to entry of the airflow into an inlet to the fan assembly. Each heat transfer element may be individually and independently fluidly isolated from the remaining heat transfer elements.
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公开(公告)号：US20200156769A1
公开(公告)日：2020-05-21
申请号：US16672606
申请日：2019-11-04
Applicant: ROLLS-ROYCE plc
Inventor： Martin N. GOODHAND
Abstract: A boundary layer ingestion fan system for location aft of the fuselage of an aircraft is shown. It comprises a nacelle defining a duct, and a fan located within the duct. The fan comprises a hub arranged to rotate around a rotational axis (A-A) and a plurality of blades attached to the hub.A blade blockage, which is the ratio of the blade thickness to the product of the circumferential pitch and the cosine of a blade inlet angle (t/s·cosβ1), is 0.25 or greater at the 0 percent span position.
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Patent Agency Ranking
公开(公告)号：US20200157944A1
公开(公告)日：2020-05-21
申请号：US16672636
申请日：2019-11-04
Applicant: ROLLS-ROYCE plc
Inventor： Martin N. GOODHAND
Abstract: A boundary layer ingestion fan system for location aft of the fuselage of an aircraft is shown. It comprises a nacelle defining a duct, and a fan located within the duct. The fan comprises a hub arranged to rotate around a rotational axis (A-A) and a plurality of blades attached to the hub, each of which has a span from a root at the hub defining a 0 percent span position (rhub) to a tip defining a 100 percent span position (rtip) and a plurality of span positions therebetween (r∈[rhub, rtip]). A hub-tip ratio of the fan, defined as the ratio of the diameter of the hub to the diameter of the fan measured at the leading edge of the blades, is from 0.45 to 0.55.
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公开(公告)号：US20200157943A1
公开(公告)日：2020-05-21
申请号：US16672591
申请日：2019-11-04
Applicant: ROLLS-ROYCE plc
Inventor： Martin N. GOODHAND
Abstract: A boundary layer ingestion fan system for location aft of the fuselage of an aircraft includes a nacelle (501) defining a duct (502), and a fan (503) located therewithin. The fan comprises a hub which rotates around a rotational axis (A-A) and a plurality of blades attached thereto. Each blade has a span (r) from a root at the hub defining a 0 percent span position (r=0) to a tip defining a 100 percent span position (r=1) and a plurality of span positions therebetween (r ∈[0, 1]), a leading edge and a trailing edge defining, for each span position, a chord therebetween having a chord length (c), and a blade thickness (t) defined for each span position thereof. For each blade, a ratio of thickness at the 0 percent span position (thub) to chord length is 0.1 or greater.
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公开(公告)号：US20200156768A1
公开(公告)日：2020-05-21
申请号：US16672584
申请日：2019-11-04
Applicant: ROLLS-ROYCE plc
Inventor： Martin N. GOODHAND
Abstract: A boundary layer ingestion fan system for location aft of the fuselage of an aircraft is shown. It comprises a nacelle (501) defining a duct, and a fan located therewithin. The fan comprises a hub arranged to rotate around a rotational axis (A-A) and a plurality of blades attached thereto. Each blade has a span (r) from a root at the hub defining a 0 percent span position (r=0) to a tip defining a 100 percent span position (r=1) and a plurality of span positions therebetween (r ∈ [0, 1]), and leading and trailing edges defining, for each span position, a chord therebetween to having a chord length (c). For each of said plurality of blades, the ratio of chord length at the 0 percent span position (chub) to chord length at the 100 percent span position (ctip) is 1 or greater.
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公开(公告)号：US20220112845A1
公开(公告)日：2022-04-14
申请号：US17484371
申请日：2021-09-24
Applicant: ROLLS-ROYCE plc
Inventor： Stephen J. BRADBROOK , Martin N. GOODHAND , Paul M. HIELD , Andrew PARSLEY , Natalie C. WONG , Robert J. CORIN , Thomas S. BINNINGTON
Abstract: A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, and an exhaust module. The fan assembly includes a plurality of fan blades defining a fan diameter (D). The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and the heat exchanger module includes a plurality of radially-extending hollow vanes arranged in a circumferential array with a channel extending axially between each pair of adjacent hollow vanes. An airflow entering the heat exchanger module is divided between a set of vane airflows through each of the hollow vanes and a set of channel airflows through each of the channels.
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公开(公告)号：US20220112840A1
公开(公告)日：2022-04-14
申请号：US17494523
申请日：2021-10-05
Applicant: ROLLS-ROYCE plc
Inventor： Stephen J. BRADBROOK , Martin N. GOODHAND , Paul M. HIELD , Andrew PARSLEY , Natalie C. WONG , Robert J. CORIN , Thomas S. BINNINGTON
Abstract: A turbofan gas turbine engine includes heat exchanger module, fan assembly, compressor, turbine and exhaust modules. The fan includes a plurality of fan blades. The heat exchanger in fluid communicates with the fan assembly by an inlet duct, and the heat exchanger includes a plurality of radially-extending hollow vanes arranged in a circumferential array, with a channel extending axially between each pair of adjacent hollow vanes. An airflow entering the heat exchanger is divided between a set of vane airflows and a set of channel airflows. Each vane airflow has a vane mass flow rate FlowVane, and each channel air flow has a channel mass flow rate FlowChan. Each hollow vane includes, an inlet, heat transfer, and exhaust portions, with the inlet portion comprising a diffuser element and the heat transfer portion including at least one heat transfer element. The diffuser element causes FlowVane to be lower than FlowChan.
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