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公开(公告)号：US09670786B2
公开(公告)日：2017-06-06
申请号：US14728618
申请日：2015-06-02
Applicant: ROLLS-ROYCE PLC
Inventor： Simon Read , Matthew D Curren
IPC: F01D5/20
CPC classification number: F01D5/20 , F05D2220/36 , F05D2260/37 , F05D2260/38 , F05D2300/501 , F05D2300/506
Abstract: A rotary blade tip insert for incorporation into a rotary blade, for example, a rotary fan blade in a gas turbine engine. The tip insert comprises a sleeve for insertion into a recess provided in said rotary blade. The sleeve has a radially outer end defining an opening, a radially inner end and opposing wall portions extending between said ends. The tip insert further comprises a tip element having a crown portion and a root portion for insertion into the opening of said sleeve.
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公开(公告)号：US20130236320A1
公开(公告)日：2013-09-12
申请号：US13799730
申请日：2013-03-13
Applicant: ROLLS-ROYCE PLC
Inventor： Peter Rowland Beckford , Simon Read , Ian Colin Deuchar Care
IPC: F01D5/14
CPC classification number: F01D5/147 , F01D5/14 , F01D21/045 , F05D2300/612
Abstract: A fan blade for a gas turbine engine has an aerofoil part and a root part. The root part includes a root former; the root former includes a zone of weakness, which reduces the ability of the root part to withstand an impact force. Thus, in an impact situation in which the fan blade has separated from the fan rotor and the fan blade has itself separated into fragments, the root part will fracture or buckle more easily than would be the case with conventional arrangements. This will lower the impact force of the root part upon the fan casing, thus permitting the fan casing to be designed to withstand lower impact forces. The fan casing can therefore be made lighter, and cheaper, than in conventional arrangements.
Abstract translation: 用于燃气涡轮发动机的风扇叶片具有机翼部分和根部部分。 根部包括根部; 根部部分包括一个弱点，这降低了根部抵抗冲击力的能力。 因此，在风扇叶片与风扇转子分离并且风扇叶片本身分离成碎片的冲击情况下，根部将比常规布置的情况更容易断裂或弯曲。 这将降低根部对风扇壳体的冲击力，从而允许风扇壳体设计成承受较低的冲击力。 因此，风扇壳体可以比常规布置更轻，更便宜。
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公开(公告)号：US10113447B2
公开(公告)日：2018-10-30
申请号：US14941095
申请日：2015-11-13
Applicant: ROLLS-ROYCE PLC
Inventor： Simon Read , Steven A Radomski
Abstract: There is proposed a fan casing arrangement for a gas turbine engine (10) of a type having a propulsive fan (12), the fan casing arrangement being configured to circumscribe the fan (12) and having a fan case (24) and a fan track liner. The fan track liner is provided around the inside of the fan case (24) so as to adopt a radial position between the fan (12) and the fan case (24), and the arrangement is configured such that the fan track liner includes a liner ring (25) which is radially outwardly biased against the inside of the fan case (24). A related method of installing a fan track liner in a gas turbine engine is also disclosed.
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Patent Agency Ranking
公开(公告)号：US08821119B2
公开(公告)日：2014-09-02
申请号：US13799730
申请日：2013-03-13
Applicant: Rolls-Royce PLC
Inventor： Peter Rowland Beckford , Simon Read , Ian Colin Deuchar Care
CPC classification number: F01D5/147 , F01D5/14 , F01D21/045 , F05D2300/612
Abstract: A fan blade for a gas turbine engine has an aerofoil part and a root part. The root part includes a root former; the root former includes a zone of weakness, which reduces the ability of the root part to withstand an impact force. Thus, in an impact situation in which the fan blade has separated from the fan rotor and the fan blade has itself separated into fragments, the root part will fracture or buckle more easily than would be the case with conventional arrangements. This will lower the impact force of the root part upon the fan casing, thus permitting the fan casing to be designed to withstand lower impact forces. The fan casing can therefore be made lighter, and cheaper, than in conventional arrangements.
Abstract translation: 用于燃气涡轮发动机的风扇叶片具有机翼部分和根部部分。 根部包括根部; 根部部分包括一个弱点，这降低了根部抵抗冲击力的能力。 因此，在风扇叶片与风扇转子分离并且风扇叶片本身分离成碎片的冲击情况下，根部将比常规布置的情况更容易断裂或弯曲。 这将降低根部对风扇壳体的冲击力，从而允许风扇壳体设计成承受较低的冲击力。 因此，风扇壳体可以比常规布置更轻，更便宜。
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公开(公告)号：US10539027B2
公开(公告)日：2020-01-21
申请号：US15204694
申请日：2016-07-07
Applicant: ROLLS-ROYCE plc
Inventor： Simon Read , Steven A Radomski
Abstract: A blade or a vane for a gas turbine engine. The blade or vane having an aerofoil and a leading edge member attached to the aerofoil. The leading edge has an electrically conductive support member and a nano-coating formed on the support member.
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公开(公告)号：USRE47696E1
公开(公告)日：2019-11-05
申请号：US15609918
申请日：2017-05-31
Applicant: Rolls-Royce plc
Inventor： Simon Read , Bijoysri Khan
Abstract: A composite aerofoil, the aerofoil having a leading edge, a trailing edge a pressure side and a suction side and comprising an outer erosion protection layer along one or both of the pressure side or suction side, a structural core having a plurality of resin impregnated plies of unidirectional fibers, and between the outer erosion protection layer and the structural core a woven composite impregnated with a resin having a modulus of elasticity greater lower than that of the resin impregnating the plies in the structural core.
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公开(公告)号：US10344774B2
公开(公告)日：2019-07-09
申请号：US15256099
申请日：2016-09-02
Applicant: ROLLS-ROYCE plc
Inventor： Steven A Radomski , Simon Read
Abstract: A gas turbine engine casing comprising: an inner circumferential wall; an outer circumferential wall spaced radially outwardly from the inner wall; wherein the inner and outer circumferential walls are formed by an axially repeating profile comprising an inner wall portion and an outer wall portion connected to one another by an intermediate portion, the axially repeating profile being arranged such that the inner wall portion abuts against and is connected to an adjacent inner wall portion to form the inner circumferential wall and the outer wall portion abuts against and is connected to an adjacent outer wall portion to form the outer circumferential wall.
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公开(公告)号：US09777599B2
公开(公告)日：2017-10-03
申请号：US14505956
申请日：2014-10-03
Applicant: ROLLS-ROYCE PLC
Inventor： Steven Aleksy Radomski , Simon Read
CPC classification number: F01D25/24 , F01D11/122 , F01D21/045 , F02C7/04 , F04D19/002 , F04D29/023 , F05D2220/36 , F05D2250/25 , F05D2300/522 , F05D2300/615 , Y10T29/49245
Abstract: A fan casing arrangement for a gas turbine engine having a propulsive fan, the arrangement having a fan case and a fan track liner and being configured to circumscribe the fan, wherein the fan track liner is provided around the inside of fan case so as to adopt a radial position between the fan and the fan case. The fan track liner includes an elongate member which is helically-wound against the inside of the fan case in a plurality of turns. A method of installing a fan track liner in a fan casing arrangement for a gas turbine engine having a propulsive fan, the method involving: providing a fan case to circumscribe the fan, providing a flexible and elongate liner member, and helically winding the liner member against the inside of the fan case in a plurality of turns to define at least part of the fan track liner.
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