GB2408295A - An assembly with a plastic insert between two metal components - Google Patents

An assembly with a plastic insert between two metal components Download PDF

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Publication number
GB2408295A
GB2408295A GB0326543A GB0326543A GB2408295A GB 2408295 A GB2408295 A GB 2408295A GB 0326543 A GB0326543 A GB 0326543A GB 0326543 A GB0326543 A GB 0326543A GB 2408295 A GB2408295 A GB 2408295A
Authority
GB
United Kingdom
Prior art keywords
compressor
attachment feature
metal component
assembly
slot
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
GB0326543A
Other versions
GB0326543D0 (en
Inventor
Thomas Gerard Mulcaire
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB0326543A priority Critical patent/GB2408295A/en
Publication of GB0326543D0 publication Critical patent/GB0326543D0/en
Publication of GB2408295A publication Critical patent/GB2408295A/en
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

An assembly, which may reduce bi-metallic corrosion, and further offer vibration damping, comprises at least one first metal component 46, a second metal component 44, and at least one plastic insert 64, 66. The first metal component 46 has at least one attachment feature 52, 54, arranged to locate in at least one slot 60, 62 in the second metal component 44. At least one plastic insert is disposed between the attachment feature(s) 52, 54 and the corresponding slot(s) 60, 62. The first metal component may be a compressor vane, and the second metal component a compressor casing of a gas turbine engine. The assembly may also be applicable to a splitter fairing.

Description

AN ASSEMBLY FOR A GAS TURBINE ENGINE
The present invention relates to an assembly for a gas turbine engine and in particular to an aerofoil assembly for a gas turbine engine.
Conventionally the radially outer ends of compressor vanes have axially extending projections, which locate in correspondingly shaped axially and circumferentially extending slots in the compressor casing. Normally metal inserts and dry lubricant is arranged between the axially extending projections on the compressor vanes and the slots in the compressor casing to reduce fretting/wear between the projections on the compressor vanes and the surfaces of the slots in the compressor casing.
There is a possibility of bimetallic corrosion between the metal insert and the compressor casing or between the metal insert and the compressor vanes.
Accordingly the present invention seeks to provide a novel insert, which reduces the above-mentioned problem.
Accordingly the present invention provides an assembly comprising at least one first metal component, a second metal component and at least one insert, the at least one first metal component having at least one attachment feature arranged to locate in at least slot in the second metal component, at least one insert arranged between the at least one first metal component attachment feature and the at least one slot in the second metal component and the at least one insert comprising a plastic material.
Preferably the at least one first metal component comprises an aerofoil.
The at least one aerofoil may comprise a compressor vane and the second metal component comprises a compressor casing.
The compressor vane may comprise a first attachment feature and a second attachment feature, the first attachment feature extending in an axially upstream direction and the second attachment feature extending in an axially downstream direction, the first attachment feature locating in a first slot in the compressor casing and a second attachment feature locating in a second slot in the compressor casing, a first insert located between the first attachment feature and the first slot and a second insert located between the second attachment feature and the second slot.
The insert may be self-lubricating.
lO The insert may comprise nylon or other suitable plastic.
There may be a plurality of compressor vanes, the first attachment feature of each compressor vane locates in the first slot in the compressor casing and the second attachment feature of each compressor vane locates in the second slot in the compressor casing.
The present invention will be more fully described by way of example with reference to the accompanying drawings in which: Figure 1 is a partially cut away view of a turbofan gas turbine engine having an aerofoil assembly according to the present invention.
Figure 2 is an enlarged cross-sectional view of an aerofoil assembly shown in figure 1.
A turbofan gas turbine engine 10, as shown in figure 1, comprises in axial flow series an intake 12, a fan section 14, a compressor section 16, a combustion section 18, a turbine section 20, and an exhaust 22. The turbine section 20 comprises one or more turbines (not shown) arranged to drive a fan rotor 24 via a shaft (not shown) and one or more turbines (not shown) arranged to drive one or more compressor rotors 40 via one or more shafts (not shown).
The fan section 14 comprises the fan rotor 24 and a plurality of circumferentially spaced radially outwardly extending fan blades 26 are carried on the fan rotor 24.
The fan rotor 24 and fan blades 26 are surrounded by a fan casing 28, which is arranged coaxially with the fan rotor 24. The fan casing 28 partially defines a fan duct 30 and the fan duct 30 has an outlet 32 at its downstream end.
The fan casing 28 is secured to a core engine casing 34 by a plurality of circumferentially spaced radially extending fan outlet guide vanes 36.
The compressor section 16 comprises a compressor rotor 40, which carries a plurality of stages of compressor l0 blades 42 and each stage of compressor blades 42 comprises a plurality of circumferentially spaced radially outwardly extending compressor blades 42. The compressor rotor 40 and compressor blades 42 are surrounded by a compressor casing 44 which is arranged coaxially around the compressor rotor 40 and compressor blades 42. The compressor casing 44 also supports a plurality of stages of compressor vanes 46 and each stage of compressor vanes 46 comprises a plurality of circumferentially spaced radially inwardly extending compressor vanes 46. The stages of compressor vanes 46 and the stages of compressor blades 42 are arranged alternately through the compressor section 16.
The turbofan gas turbine engine 10 operates conventionally and its operation will not be discussed further.
One of the compressor vanes 46 and a portion of the compressor casing 44 is shown more clearly in figure 2 and the compressor vane 46 comprises an aerofoil portion 48 and an attachment portion, also known as a platform, 50. The attachment portion 50 is secured to the compressor casing 44. The attachment portion 50 comprises a first projection 52, which extends in an upstream direction and a second projection 54, which extends in a downstream direction.
The compressor casing 44 is provided with a first hook 56, which extends in a radially inward and an axially downstream direction and a second hook 58, which extends in a radially inward and an axially upstream direction. The second hook 58 is arranged axially downstream of the first hook 56. Generally the first and second hooks 56 and 58 respectively are annular and hence define first and second annular recesses 60 and 62 respectively with the inner surface of the compressor casing 44.
The attachment portion 50 of the compressor vane 46 locates axially between the first and second hooks 56 and 58 and the first projection 52 locates in the first annular recess 60 and the second projection 54 locates in the second annular recess 62.
In addition a first insert 64 is arranged in the first recess 60 between the first projection 52 and the first hook 56 and the inner surface 68 of the compressor casing 44 and a second insert 66 is arranged in the second recess 62 between the second projection 54 and the second hook 58 and the inner surface 68 of the compressor casing 44.
The compressor vane 46 and the compressor casing comprise a metal, for example titanium, titanium alloy, aluminium or steel. The first and second inserts 64 and 66 respectively comprise a plastic material, for example nylon.
The first and second inserts 64 and 66 respectively have the advantage of dispensing with the requirement for a dry film lubricant. The first and second inserts 64 and 66 respectively eliminate the possibility of bimetallic corrosion occurring between the first and second inserts 64 and 66 and the compressor vane 46 and/or the compressor casing 44. Additionally the first and second inserts 64 and 66 may provide vibration damping of the compressor vanes 46.
Each compressor vane 46 may have its own attachment portion 50, but alternatively a plurality of compressor vanes 46 may share a common attachment portion 50.
Similarly each compressor vane 46 may have an attachment portion at its radially inner end for securing to an inner ring structure in a similar manner.
The present invention is also applicable to an assembly where a first casing portion has a projection locating in a slot in a second casing portion, for example the splitter fairing.
The present invention is also applicable to other assemblies of two metal components where a first metal component has an attachment feature, which locates in a slot in a second metal component.

Claims (9)

  1. Claims: 1. An assembly comprising at least one first metal component, a
    second metal component and at least one insert, the at least one first metal component having at least one attachment feature arranged to locate in at least slot in the second metal component, at least one insert arranged between the at least one first metal component attachment feature and the at least one slot in the second metal component and the at least one insert comprising a plastic material.
  2. 2. An assembly as claimed in claim 1 wherein the at least one first metal component comprises an aerofoil.
  3. 3. An assembly as claimed in claim 2 wherein the at least one aerofoil comprises a compressor vane and the second metal component comprises a compressor casing.
  4. 4. An assembly as claimed in claim 3 wherein the at least one compressor vane comprises a first attachment feature and a second attachment feature, the first attachment feature extending in an axially upstream direction and the second attachment feature extending in an axially downstream direction, the first attachment feature locating in a first slot in the compressor casing and a second attachment feature locating in a second slot in the compressor casing, a first insert located between the first attachment feature and the first slot and a second insert located between the second attachment feature and the second slot.
  5. 5. An assembly as claimed in any of claims 1 to 4 wherein the insert is self-lubricating.
  6. 6. An assembly as claimed in any of claims 1 to 5 wherein the insert comprises nylon.
  7. 7. An assembly as claimed in claim 4 wherein there are a plurality of compressor vanes, the first attachment feature of each compressor vane locates in the first slot in the compressor casing and the second attachment feature of each compressor vane locates in the second slot in the compressor casing.
  8. 8. An assembly substantially as hereinbefore described with reference to and as shown in figure 2 of the accompanying drawings.
  9. 9. A gas turbine engine comprising an assembly as claimed in any of claims 1 to 8.
GB0326543A 2003-11-14 2003-11-14 An assembly with a plastic insert between two metal components Withdrawn GB2408295A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB0326543A GB2408295A (en) 2003-11-14 2003-11-14 An assembly with a plastic insert between two metal components

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB0326543A GB2408295A (en) 2003-11-14 2003-11-14 An assembly with a plastic insert between two metal components

Publications (2)

Publication Number Publication Date
GB0326543D0 GB0326543D0 (en) 2003-12-17
GB2408295A true GB2408295A (en) 2005-05-25

Family

ID=29726526

Family Applications (1)

Application Number Title Priority Date Filing Date
GB0326543A Withdrawn GB2408295A (en) 2003-11-14 2003-11-14 An assembly with a plastic insert between two metal components

Country Status (1)

Country Link
GB (1) GB2408295A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2450934A (en) * 2007-07-13 2009-01-14 Rolls Royce Plc A component with a damping filler
US8241004B2 (en) 2008-05-15 2012-08-14 Rolls-Royce, Plc Component structure
US8365388B2 (en) 2009-01-28 2013-02-05 Rolls-Royce Plc Method of joining plates of material to form a structure
US8529720B2 (en) 2008-07-24 2013-09-10 Rolls-Royce, Plc Aerofoil sub-assembly, an aerofoil and a method of making an aerofoil
US8701286B2 (en) 2010-06-02 2014-04-22 Rolls-Royce Plc Rotationally balancing a rotating part
US8920893B2 (en) 2009-01-27 2014-12-30 Rolls-Royce Plc Article with an internal structure
US8986490B2 (en) 2010-11-26 2015-03-24 Rolls-Royce Plc Method of manufacturing a component

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB836030A (en) * 1955-10-31 1960-06-01 Maschf Augsburg Nuernberg Ag Improvements in or relating to a turbine blade and rotor assembly
US3784320A (en) * 1971-02-20 1974-01-08 Motoren Turbinen Union Method and means for retaining ceramic turbine blades
JPH0821201A (en) * 1994-07-04 1996-01-23 Ishikawajima Harima Heavy Ind Co Ltd Cushioning material of turbine moving blade implanting part
US6431835B1 (en) * 2000-10-17 2002-08-13 Honeywell International, Inc. Fan blade compliant shim

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB836030A (en) * 1955-10-31 1960-06-01 Maschf Augsburg Nuernberg Ag Improvements in or relating to a turbine blade and rotor assembly
US3784320A (en) * 1971-02-20 1974-01-08 Motoren Turbinen Union Method and means for retaining ceramic turbine blades
JPH0821201A (en) * 1994-07-04 1996-01-23 Ishikawajima Harima Heavy Ind Co Ltd Cushioning material of turbine moving blade implanting part
US6431835B1 (en) * 2000-10-17 2002-08-13 Honeywell International, Inc. Fan blade compliant shim

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2450934A (en) * 2007-07-13 2009-01-14 Rolls Royce Plc A component with a damping filler
GB2450934B (en) * 2007-07-13 2009-10-07 Rolls Royce Plc A Component with a damping filler
US8182233B2 (en) 2007-07-13 2012-05-22 Rolls-Royce Plc Component with a damping filler
US8381398B2 (en) 2007-07-13 2013-02-26 Rolls-Royce Plc Component with a damping filler and method
US8857054B2 (en) 2007-07-13 2014-10-14 Rolls-Royce Plc Method of forming an aerofoil with a damping filler
US8241004B2 (en) 2008-05-15 2012-08-14 Rolls-Royce, Plc Component structure
US8529720B2 (en) 2008-07-24 2013-09-10 Rolls-Royce, Plc Aerofoil sub-assembly, an aerofoil and a method of making an aerofoil
US8920893B2 (en) 2009-01-27 2014-12-30 Rolls-Royce Plc Article with an internal structure
US8365388B2 (en) 2009-01-28 2013-02-05 Rolls-Royce Plc Method of joining plates of material to form a structure
US8701286B2 (en) 2010-06-02 2014-04-22 Rolls-Royce Plc Rotationally balancing a rotating part
US8986490B2 (en) 2010-11-26 2015-03-24 Rolls-Royce Plc Method of manufacturing a component

Also Published As

Publication number Publication date
GB0326543D0 (en) 2003-12-17

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WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)