Patent Publication Number: US-11035241-B2

Title: Method to pilot using flexible profile

Description:
CROSS-REFERENCE TO RELATED APPLICATION 
     This application is a continuation of U.S. patent application Ser. No. 14/935,938, filed Nov. 9, 2015, which in turn claims the benefit of and priority to U.S. Provisional Patent Application Ser. No. 62/087,958, filed Dec. 5, 2014, both of which are incorporated herein by this reference in their entirety. 
    
    
     FIELD OF THE DISCLOSURE 
     The present disclosure relates generally to gas turbine engines and more specifically to attachment of gas turbine engine components. 
     BACKGROUND 
     Gas turbine engines are used to power aircraft, watercraft, power generators, and the like. Gas turbine engines typically include a compressor, a combustor, and a turbine. The compressor compresses air drawn into the engine and delivers high pressure air to the combustor. In the combustor, fuel is mixed with the high pressure air and is ignited. Products of the combustion reaction in the combustor are directed into the turbine where work is extracted to drive the compressor and, sometimes, an output shaft. Left-over products of the combustion are exhausted out of the turbine and may provide thrust in some applications. 
     Gas turbine engines used in aircraft may include a fan assembly that is driven by the turbine to push air through the engine and provide thrust for the aircraft. A typical fan assembly includes a fan disk having blades and a fan case that extends around the blades of the fan disk. During operation, the fan blades of the fan disk are rotated to push air through the engine. The fan case guides the air pushed by the fan blades. 
     The fan assembly may further include a windage shield coupled to the fan disk to assist in guiding air through the engine. The windage shield may be positioned to block entry of high pressure air into ambient environments within the gas turbine engine. Harmful stresses may form in the windage shield during operation of the gas turbine engine. These stresses may result from high rotational speeds of the fan assembly or from differences in thermal and mechanical expansion rates between the windage shield and the fan disk. 
     SUMMARY 
     The present disclosure may comprise one or more of the following features and combinations thereof. 
     A gas turbine engine may include a first component configured to rotate about a rotational axis, a second component coupled to the first component to rotate about the rotational axis with the first component, and a pilot unit coupled to the second component to move therewith. The first component may include a first axial surface and a pilot receiver extending axially from the first axial surface. The pilot unit may be arranged to extend downwardly and engage the pilot receiver. 
     The pilot unit may include a pilot mount appended to the second component and arranged to extend toward the pilot receiver, a pilot anchor located in spaced-apart radial relation to the pilot mount and arranged to engage the pilot receiver, and a bias link arranged to extend between and interconnect the pilot mount and the pilot anchor. The bias link may be configured to provide means for maintaining a pilot-setting force between the pilot anchor and the pilot receiver when the second component is coupled to the first component to retain alignment of the first component with the second component for rotation about the rotational axis while minimizing stress formed in the bias link as a result of first component having a different thermal or mechanical expansion rate from the second component during operation of the gas turbine engine. 
     In some embodiments, the bias link may include a first end appended the pilot mount, an opposite second end located in spaced-apart relation to the first end and appended to the pilot anchor, and an inner surface arranged to extend between and interconnect the first and second ends of the bias link, face toward the first component, and have a curved shape. 
     In some embodiments, the curved shape is concave extending radially outward away from the first component. 
     In some embodiments, the bias link may further include an outer surface spaced apart axially from the inner surface, arranged to extend between and interconnect the first and second ends of the bias link, arranged to face away from the second component, and have a curved shape. 
     In some embodiments, the curved shape of the inner surface and the outer surface is concave and arranged to extend outwardly way from the first component. 
     In some embodiments, the pilot unit may further include an outer tab coupled to the pilot mount opposite of the first component and extending axially away from the pilot mount and the bias link is coupled to the pilot mount and the outer tab. 
     In some embodiments, the pilot unit may further include an inner tab coupled to the pilot anchor and arranged to extend radially inward of the pilot anchor. 
     In some embodiments, the bias link may include a substantially straight section extending radially inward from the pilot mount and a curved section extending between the substantially straight section and the pilot anchor. 
     In some embodiments, the pilot unit may further include a pilot support coupled between the curved section of the bias link and the inner tab. 
     In some embodiments, the pilot unit may further include a pilot support coupled between the bias link and the pilot anchor to form a channel between the bias link and the inner tab. 
     In some embodiments, the bias link may be coupled to the pilot anchor and inner tab. 
     In some embodiments, the pilot unit may further include an inner tab coupled to the pilot anchor and arranged to extend radially inward of the pilot anchor. 
     In some embodiments, the pilot unit may further include a pilot support coupled between the bias link and the pilot anchor to form a channel between the bias link and the inner tab. 
     In some embodiments, the pilot unit may further include a pilot support coupled between the bias link and the inner tab. 
     In some embodiments, the pilot anchor may be positioned radially outward of the pilot receiver. 
     In some embodiments, a radial distance between the pilot anchor and pilot mount may increase when the first and second components are heated to an operational temperature of the gas turbine engine. 
     In some embodiments, the pilot anchor may be arranged to contact the axial surface of the first component to space the pilot mount from the axial surface of the first component at a first axial distance. 
     In some embodiments, the bias link may be arranged to elastically deform when the second component is coupled to the first component to position the pilot mount a lesser second axial distance from the first component and to bias the pilot mount away from the first component. 
     According to another aspect of the present disclosure, a process of coupling a first component to a second component in a gas turbine engine may include the steps of arranging a first component and a second component along a central axis of the gas turbine engine, contacting a first portion of the second component against the first component to align the second component relative to the first component, biasing a second portion of the second component toward the first component to elastically deform a third portion of the second component coupled between the first and second portions to force the first portion against the first component, and retaining the second component on the first component such that contact between the first portion of the second component and the first component is maintained as radial loads placed on the second component vary during operation of the gas turbine engine. 
     In some embodiments, the first portion of the second component may be a pilot anchor, the first component may include an axial surface and a pilot receiver extending axially from the axial surface, and the contacting step may include contacting the pilot anchor with the pilot receiver and contacting the pilot anchor with the axial surface. 
     According to another aspect of the present disclosure, a gas turbine engine may include a fan disk arranged to hold a plurality of fan blades for rotation about a central axis of the gas turbine engine, a windage shield coupled to the fan disk to move therewith, and a pilot unit coupled to the windage shield to move therewith. The fan disk may be formed to include an axial wall and a pilot receiver extending axially from the axial wall. The windage shield may be arranged to guide incoming air provided by the fan blades through the gas turbine engine. The pilot unit may be arranged to extend downwardly and engage the pilot receiver. 
     The pilot unit may include a pilot mount appended to the windage shield and arranged to extend toward the pilot receiver, a pilot anchor located in spaced-apart radial relation to the pilot mount and arranged to engage the pilot receiver and axial wall of the fan disk, and a bias link arranged to extend between and interconnect the pilot mount and the pilot anchor. The bias link may be arranged to elastically deform to force the pilot anchor against the pilot receiver and axial wall of the fan disk to maintain alignment of the windage shield with the fan disk during operation of the gas turbine engine. 
     In some embodiments, the pilot unit may further include an outer tab appended to the pilot mount and arranged to extend axially from the pilot mount. The bias link may include a first end appended the pilot mount and outer tab, an opposite second end located in spaced-apart relation to the first end and appended to the pilot anchor, and an inner surface arranged to extend between and interconnect the first and second ends of the bias link, face toward the first component, and have a curved shape. 
     In some embodiments, the pilot unit may further include an inner tab appended to the pilot anchor and arranged to extend radially inward from the pilot anchor, a pilot support appended between the second end of the bias link and the inner tab and arranged to form a channel between the bias link and inner tab. 
     These and other features of the present disclosure will become more apparent from the following description of the illustrative embodiments. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG. 1  is a perspective view of a gas turbine engine with portions broken away showing that the gas turbine engine includes fan blades attached to a fan disk and a windage shield coupled to the fan disk by a plurality of component anchors for rotation about a central axis of the gas turbine engine; 
         FIG. 2  is an enlarged cross-sectional view of the fan disk and windage shield of  FIG. 1  showing that the component anchors interconnect the windage shield to the fan disk to rotate therewith and suggesting that a pilot anchor of the windage shield is held against a pilot receiver of the fan disk at a distance from the component anchor (W) and there is a low radial load on the component anchor when there is a low temperature and low rotational speed of the fan disk and windage shield; 
         FIG. 3  is a view similar to  FIG. 2  suggesting that the pilot anchor remains in contact with the pilot receiver at substantially the same distance from the component anchor (W) and the radial load on the anchor remains low as the fan disk radially expands relative to the windage shield with rising temperature and rotational speed of the fan disk and windage shield; 
         FIG. 4  is an exploded assembly view of the fan disk and windage shield of  FIG. 1  showing one embodiment of a pilot unit of the windage shield in accordance with the present disclosure and suggesting that the pilot unit includes the pilot anchor, a pilot mount, and a bias link interconnecting the pilot anchor and pilot mount; 
         FIG. 5  is an exploded cross-sectional view of the assembly of  FIG. 4  showing one embodiment of a component anchor in accordance with the present disclosure and suggesting that the pilot anchor is positioned to engage with the pilot receiver to align the windage shield with the fan disk and that the component anchor includes, from left to right, a fastener retainer, a bushing, a washer, and a fastener; 
         FIG. 6  is a cross-sectional view of the component anchor of  FIG. 5  showing the windage shield coupled to the fan disk by the component anchor and suggesting that a first and second gap are configured between portions of the windage shield (A 1 ) and the anchor (B 1 ) as the component anchor is installed forcing the pilot unit against the fan disk (F A1 ); 
         FIG. 7  is a view similar to  FIG. 6  showing that tightening the fastener reduces the second gap (B 2 ) formed between the washer and bushing and the first gap (A 2 ) formed between the windage shield and the fan disk at a similar rate and further forces the pilot anchor against the fan disk (F A2 ); 
         FIG. 8  is a view similar to  FIG. 7  suggesting that further tightening of the fastener forces the washer to contact the bushing while the first gap (A 3 ) between windage shield and fan disk remains and elastically deforms the bias link of the pilot unit to further force the pilot anchor against the fan disk (F A3 ) and against the pilot receiver (F R1 ) at a distance from the component anchor (W); 
         FIG. 9  is a view similar to  FIG. 8  suggesting that the bias link contracts radially with the windage shield as the temperature and rotational speed of the fan disk increase to reduce and outer gap (D 1 -D 2 ) and increase an inner gap (C 1 -C 2 ) formed between the bushing and an anchor-receiving space formed in the windage shield due to a differential in thermal and mechanical expansion rates between the windage shield and the fan disk while the radial load on the fastener remains low and that the force between the pilot anchor and pilot receiver is increased (F 2 ) while the pilot anchor is maintained at substantially the same distance from the component anchor (W); 
         FIG. 10  is a view similar to  FIG. 9  suggesting that the bias link expands radially with the windage shield as the temperature and rotational speed of the fan disk decrease to reduce the inner gap (C 2 -C 3 ) and increase the outer gap (D 2 -D 3 ) while a radial load on the fastener remains low and that the force between the pilot anchor and pilot receiver is reduced (F 3 ) while the pilot anchor is maintained at substantially the same distance from the component anchor (W); 
         FIG. 11  is a cross-sectional view of the pilot unit of the windage shield of  FIG. 8  showing the stresses within the pilot unit and suggesting that high stresses are placed on the bias link rather than on the rest of the windage shield; 
         FIG. 12  is a cross-sectional view of anther embodiment of a pilot unit of the windage shield in accordance with the present disclosure; 
         FIG. 13  is a cross-sectional view of anther embodiment of a pilot unit of the windage shield in accordance with the present disclosure; 
         FIG. 14  is a cross-sectional view of anther embodiment of a pilot unit of the windage shield in accordance with the present disclosure; 
         FIG. 15  is a cross-sectional view of anther embodiment of a pilot unit of the windage shield in accordance with the present disclosure; 
         FIG. 16  is a cross-sectional view of anther embodiment of a pilot unit of the windage shield in accordance with the present disclosure; 
         FIG. 17  is a cross-sectional view of anther embodiment of a pilot unit of the windage shield in accordance with the present disclosure; 
         FIG. 18  is a cross-sectional view of the assembly of  FIG. 4  showing an alternative attachment arrangement for coupling the windage shield to the fan disk and suggesting that there is no gap between windage shield and fan disk; 
         FIG. 19  is a chart showing stresses placed on a flange of the fan disk compared to stresses placed on a fillet of a reference pilot unit in accordance with the present disclosure and an aft side of the reference pilot unit when various coefficients of friction are assumed; 
         FIG. 20  is a chart showing stresses placed on a flange of the fan disk compared to stresses placed on a fillet of the pilot unit of  FIG. 18  and an aft side of the pilot unit when various coefficients of friction are assumed; 
         FIG. 21  is a chart showing axial deflections of the pilot anchor relative to the fan disk and the radial deflections of the pilot anchor relative to the pilot receiver and suggesting that the pilot anchor remains in a substantially constant position relative to the fan disk and pilot receiver during operation of the gas turbine engine; 
         FIG. 22  is a chart showing the axial loads on the windage shield, fastener, and bushing during assembly and operation of the gas turbine and suggesting that tightening the fastener places a low axial load on the windage shield which remains substantially constant during operation of the gas turbine engine; 
         FIG. 23  is a chart similar to  FIG. 21  showing the radial loads on the windage shield and fastener and suggesting that the radial load on the fastener remains low as the radial load on the windage shield changes during operation of the gas turbine engine; 
         FIG. 24  is an exploded cross-sectional view of another embodiment of an anchor in accordance with the present disclosure showing that the anchor includes, from left to right, a fastener retainer, a bushing, an insert, a washer, and a fastener; 
         FIG. 25  is a cross-sectional view of the anchor of  FIG. 24  showing the windage shield coupled to the fan disk by the anchor and suggesting that the stresses in the anchor are minimized as a result of several gaps being configured between portions of the windage shield and the anchor; 
         FIG. 26  is a perspective view of one embodiment of a bushing in accordance with the present disclosure; 
         FIG. 27  is a cross-sectional view of another embodiment of an anchor in accordance with the present disclosure showing that the anchor includes, from left to right, a fastener retainer, the bushing of  FIG. 26 , and a fastener and suggesting that the stresses in the anchor are minimized as a result of several gaps being configured between portions of the windage shield and the anchor; 
         FIG. 28  is a perspective view of one embodiment of a fastener in accordance with the present disclosure; and 
         FIG. 29  is a cross-sectional view of another embodiment of an anchor in accordance with the present disclosure showing that the anchor includes, from left to right, a fastener retainer and the fastener of  FIG. 28 , and suggesting that the stresses in the anchor are minimized as a result of several gaps being configured between portions of the windage shield and the anchor. 
     
    
    
     DETAILED DESCRIPTION OF THE DRAWINGS 
     For the purposes of promoting an understanding of the principles of the disclosure, reference will now be made to a number of illustrative embodiments illustrated in the drawings and specific language will be used to describe the same. 
     FIRST ASPECT OF THE DISCLOSURE 
     An illustrative gas turbine engine  100  used in aircraft includes a fan assembly  130  driven by an engine core  120  to push air through the engine  100  and provide thrust for the aircraft as suggested in  FIG. 1 . The illustrative fan assembly  130  includes a fan disk  113 , also called a first component  113 , having a number of fan blades  115 , a fan case  131  that extends around the fan blades  115  of the fan disk  113 , a static vane assembly  133  for directing air through the engine  100 , and a windage shield  117 , also called a second component  117 , coupled between the fan disk  113  and static vane assembly  133 . A number of flow guides  119  are secured to the fan disk  113  between the fan blades  115  to force incoming air outwards toward the windage shield  117 . 
     The windage shield  117  is coupled to the fan disk  113  by one or more component anchors  10  for rotation about a central axis  111  of the engine  100  as suggested in  FIGS. 2 and 3 . The windage shield  117  includes an outer annular shield wall  22 , a radially extending support wall  24  coupled to the shield wall  22 , and a pilot unit  26  coupled to the support wall  24 . The shield wall  22  is positioned to span a gap  135  between the flow guides  119  and static vane assembly  133 . The shield wall  22  blocks incoming air passing over the flow guides  119  from passing through the gap  135  and entering an ambient environment  139  within the engine  100 . The incoming air instead passes over the shield wall  22  and over the static vane assembly  133  to other areas of the engine  100 , such as the engine core  120 . The support wall  24  couples the shield wall  22  to the pilot unit  26  and positions the shield wall  22  over portions of the flow guides  119  and static vane assembly  133  so that the incoming air may flow over the shield wall  22 . 
     The fan disk  113  and windage shield  117  radially expand as the rotational speed and temperature of the gas turbine engine  100  increases as shown in  FIG. 3 . The static vane assembly  134  remains at a substantially constant radius from the axis of rotation  111 . However, it should be noted that variations in the radius of the static vane assembly  134  may occur due to changes in temperature within the gas turbine engine  100 . As such, an opening may be formed between the shield wall  22  of the windage shield  117  and static vane assembly  134  which allows gases trapped in the ambient environment  139  to escape through the gap  135  and into other sections of the engine  100 . 
     In one illustrative embodiment, the pilot unit  26  includes a pilot mount  27  coupled to the support wall  24 , a bias link  28  coupled to the pilot mount  27  and extending radially inward from the pilot mount  27 , and a pilot anchor  29  coupled to the bias link  28  as shown in  FIGS. 2-3 . The pilot unit  26  cooperates with the fan disk  113  to align rotation of the windage shield  117  with the fan disk  113 . The component anchors  10  pass through the pilot mount  27  and through flanges  32  of the fan disk  113  to couple the windage shield  117  to the fan disk  113 . A radially extending wall  36  and pilot receiver  34  of the fan disk  113  cooperate with the pilot mount  27  of the windage shield  117  to align the windage shield  117  with the fan disk  113 . 
     The bias link  28  includes a first end  81  coupled to the pilot mount  27 , a second end  83  coupled to the pilot anchor  29 , a first curved surface  85  extending between the first and second ends  81 ,  83 , and a second curved surface  86  spaced apart from the first curved surface  85  and extending between the first and second ends  81 ,  83  as shown in  FIG. 5 . The bias link  28  assumes a generally curved shape with the curve extending away from the fan disk  113 . However, any other suitable shape may be used. The pilot unit  26  further includes an outer tab  21  coupled to the pilot mount  27  and extending axially outward therefrom. The first end  81  of the bias link  28  is coupled to the pilot mount  27  and outer tab  21 . However, the first end  81  is coupled to the pilot mount  27  alone. In one embodiment, the outer tab  21  is a balance land where portions are machined away to balance the windage shield  117  for rotation. 
     The pilot anchor  29  includes a radially-extending contact surface  71 , a radially-extending support surface  73  spaced apart from the contact surface  71 , an axially-extending coupler surface  75  coupled between the contact and support surfaces  71 ,  73 , an axially-extending mount surface  77  spaced apart from the coupler surface  75  and coupled to the support surface  73 , and a bevel surface  76  coupled between the contact surface  71  and mount surface  77  as shown in  FIG. 5 . The second end  83  of the bias link  28  is coupled to the coupler surface  75 . In the illustrative embodiment, the pilot anchor  29  further includes an inner tab  23  coupled to the support surface  73  and a pilot support  41  coupled between the bias link  28  and inner tab  23 . The pilot support  41  forms a channel  43  between the bias link  28  and inner tab  23 . In one embodiment, the inner tab  23  is a removal feature allowing the windage shield  117  to be pried off of the fan disk  113 . 
     The pilot receiver  34  of the fan disk  113  includes a receiver surface  91  extending axially from the wall  36 , a radially-extending end surface  93 , and an angled guide surface  95  coupled between the receiver surface  91  and end surface  93  as shown in  FIG. 5 . In the illustrative embodiment, the mount surface  77  of the pilot anchor  29  and the receiver surface  91  of the pilot receiver  34  are positioned at substantially the same radial distance from the central axis  111  of the engine  100  such that the mount surface  77  mates with the receiver surface  91  to align the windage shield  117  with the fan disk  113  as suggested in  FIG. 6 . In another embodiment, the mount surface  77  is positioned radially inward of the receiver surface  91  such that the pilot anchor  29  may be press fit around the pilot receiver  34 . The bevel surface  76  of the pilot anchor  29  may engage the guide surface  95  of the pilot receiver  34  to guide the windage shield  117  into alignment with the fan disk  113  during installation. 
     Each component anchor  10  includes a fastener  12 , a washer  14 , a bushing  16 , and a fastener retainer  18  as shown in  FIG. 5 . The component anchor  10  is installed along an installation axis  150  through the windage shield  117  and the fan disk  113 . The fastener  12  includes a head  52  and a shaft  54  coupled to the head  52 . The shaft  54  includes a substantially smooth neck section  58  and an engagement section  56  arranged to couple the fastener  12  to the fastener retainer  18 . In the illustrative embodiment, the engagement section  56  and fastener retainer  18  are threaded. However, it should be noted that other arrangements for coupling the fastener  12  with the fastener retainer  18  are contemplated, such as a key, pin, spring clip, or other suitable alternative. 
     The washer  14  includes an annular body  62  and a fastener-receiving aperture  64  formed through the annular body  62 . The annular body  62  includes an engagement surface  66  and a retainer surface  68 . The engagement surface  66  is arranged to contact the bushing  16  and the pilot mount  27  of the windage shield  117 . The retainer surface  68  is arranged to contact the head  52  of the fastener  12  to force the washer  14  against the bushing  16  and pilot mount  27 . The pilot mount  27  includes an anchor-receiving passageway  72  formed through the pilot mount  27 . The washer  14  has a larger outer diameter than the anchor-receiving passageway  72  such that the washer  14  does not pass through the anchor-receiving passageway  72 . 
     The bushing  16  includes a sleeve  82  and a flange  84  coupled to one end of the sleeve  82  as shown in  FIG. 5 . The sleeve  82  has a smaller diameter than the anchor-receiving passageway  72  such that the sleeve  82  may pass through the anchor-receiving passageway  72  to contact the washer  14 . A length of the bushing  16  is generally longer than the length of the anchor-receiving passageway  72 . For example, the sleeve  82  may extend through the anchor-receiving passageway  72  to contact the washer  14  on one side of the pilot mount  27  while the flange  84  contacts the fan disk  113  on an opposing side of the pilot mount  27  as shown in  FIG. 8 . The pilot mount  27  further include a recess  74  formed at one end of the anchor-receiving passageway  72 . The recess  74  may be sized and arranged to surround the flange  84  of the bushing  16 . 
     The fastener retainer  18  includes an annular retainer body  92  and an inner engagement surface  94  as shown in  FIG. 5 . The inner engagement surface  94  is arranged to couple with the engagement section  56  of the fastener  12 . The annular retainer body  92  is sized and arranged to contact the flange  32  of the fan disk  113  such that the retainer body  92  does not pass through an aperture  38  formed in the flange  32 . In an alternative embodiment, the fastener  12  may be coupled directly to the flange  32  of the fan disk  113  without the use of the fastener retainer  18 . 
     The windage shield  117  is coupled to the fan disk  113  by assembling the component anchor  10  as suggested in  FIGS. 6-8 . The windage shield  117  is aligned with the fan disk  113  such that the aperture  38  of the fan disk  113  and the anchor-receiving passageway  72  of the windage shield  117  are aligned along the installation axis  150 . The fastener  12  passes along the installation axis  150  through the washer  14 , the anchor-receiving passageway  72  of the windage shield  117 , the bushing  16 , and flange  32  of the fan disk  113  to engage the fastener retainer  18 . 
     The fastener  12  engages the fastener retainer  18  to force the washer  14  against the pilot mount  27  of the windage shield  117  as suggested in  FIG. 6 . In the illustrative embodiment, the component anchor  10  positions the windage shield  117  relative to the fan disk  113  such that the pilot mount  27  of the windage shield  117  is spaced apart from the radially extending wall  36  of the fan disk  113  at a distance A 1  prior to the fastener  12  being tightened. Distance A 1  is also called gap A 1 . At the same time, the washer  14  is spaced apart from the bushing  16  at a corresponding distance B 1 , also called gap B 1 . The distances A 1  and B 1  decrease at a substantially similar rate as the fastener  12  is tightened relative to the fastener retainer  18  as suggested in  FIG. 7 . For example, distance A 1  decreases to a distance A 2  as the fastener  12  is tightened and the distance B 1  decreases by substantially the same amount to a distance B 2 . Additional tightening of the fastener  12  forces the washer  14  to contact the bushing  16  which forces the bushing  16  against the fan disk  113  to move the windage shield  117  to a distance A 3  from the fan disk  113  as suggested by  FIG. 8 . The fastener  12  may then be further tightened to an operating tension to retain the windage shield  117  on the fan disk  112  during operation of the gas turbine engine  100 . 
     The bias link  28  may elastically deform during installation of the component anchor  10  as the gap A 1  decreases to gap A 3  as suggested in  FIGS. 6-8 . In the illustrative embodiment, the contact surface  71  of the pilot anchor  29  engages the radially extending wall  36  of the fan disk  113  with an initial force F A1 . Tightening of the fastener  12  forces the pilot mount  27  to move relative to the pilot anchor  29  and elastically deform the bias link  28  as the pilot anchor  29  is further force against the fan disk  113  to a force F A2 . The curved profile of the bias link  28  causes the bias link  28  to act as a spring form and deformation of the bias link  28  forces the mount surface  77  of the pilot anchor  29  against the receiver surface  91  of the pilot receiver  34  with a force F R1  as suggested in  FIG. 8 . Upon completed installation, the pilot anchor  29  may be forced against the fan disk  113  to a force F A3  which is relatively higher than force F A2 . The inner tab  23  may be spaced apart from the end surface  93  of the pilot receiver  34  when contact surface  71  of the pilot anchor  29  contacts the wall  36  of the fan disk  113 . 
     The bias link  28  maintains the pilot anchor  29  at a substantially constant distance W from the component anchor  10  during operation of the gas turbine engine  100  as suggested in  FIGS. 8-10 . The component anchor  10  is sized to allow for radial expansion and contraction of the windage shield  117 . A radially inner gap C 1  and a radially outer gap D 1  are formed between the sleeve  82  and the anchor-receiving passageway  72  when the component anchor  10  is assembled and the windage shield  117  is coupled to the fan disk  113  as shown in  FIG. 8 . In the illustrative embodiment, the gaps C 1  and D 1  are substantially the same size when the temperature and rotational speed of the windage shield  117  are low, for example, prior to operation of the engine  100 . 
     The fan disk  113  may radially expand during operation of the gas turbine engine  100  increasing the size of gap C 1  to a gap C 2  and decreasing the size of gap D 1  to a gap D 2  as suggested in  FIG. 9 . The fan disk  113  may expand due to increased rotational speed and/or temperature. A relative expansion between the fan disk  113  and windage shield  117  may occur. For example, the fan disk  113  may be made of titanium while the windage shield  117  is made of aluminum. The difference in the coefficients of thermal expansion and modulus of elasticity between the materials may cause the fan disk  113  to expand further or more rapidly than the windage shield  117 . For example, the weight of the fan blades  115  attached to the fan disk  113  places a greater load on the fan disk  113  than the shield wall  22  and support wall  24  place on the pilot unit  26  of the windage shield  117  forcing the fan disk  113  to expand faster than the windage shield  117 . 
     As such, the bias link  28  may also radially contract as suggested in  FIG. 9 . Radial contraction of the bias link  28  increases the force applied by the bias link  28  to the pilot anchor  29  to a force F R2 . The force F R2  maintains the pilot anchor  29  at the distance W from the component anchor  10  such that the mount surface  77  remains in contact with the receiver surface  91  and maintains alignment of the windage shield  117  relative to the fan disk  113 . Additionally, the force F R2  creates a frictional force between the mount surface  77  and receiver surface  91 . The friction force maintains tangential alignment of the windage shield  117  with the fan disk  113 . 
     The fan disk  113  may radially contract during run down of the gas turbine engine  100  decreasing the size of gap C 2  to a gap C 3  and increasing the size of gap D 2  to a gap D 3  as suggested in  FIG. 10 . The fan disk  113  may contract due to reduced rotational speed and temperature. A relative contraction between the fan disk  113  and windage shield  117  may occur. For example, the fan disk  113  may be made of titanium while the windage shield  117  is made of aluminum. The difference in the coefficients of thermal expansion and modulus of elasticity between the materials may cause the fan disk  113  to contract further or more rapidly than the windage shield  117 . For example, the windage shield  117  may remain in a hot and expanded state longer than the fan disk  113 . 
     The bias link  28  may also radially expand as suggested in  FIG. 10 . Radial expansion of the bias link  28  decreases the force applied by the bias link  28  to the pilot anchor  29  to a force F 3 . However, the force F R3  is large enough to maintain the pilot anchor  29  at the distance W from the component anchor  10  such that the mount surface  77  remains in contact with the receiver surface  91  and maintains alignment of the windage shield  117  relative to the fan disk  113 . Additionally, the force F R3  creates a frictional force between the mount surface  77  and receiver surface  91 . The friction force maintains tangential alignment of the windage shield  117  with the fan disk  113 . 
     The pilot unit  26  relieves the stresses of maintaining alignment of the windage shield  117  with the fan disk  113  by placing them in the bias link  28  and pilot anchor  29  as suggested in  FIG. 11 . A fillet  87  may be formed between the first end  81  of the bias link  28  and the pilot mount  27 . As suggested in  FIG. 11 , the fillet  87  may carry a high stress as compared to the pilot mount  27 . For example, the first end  81  of the bias link  28  and fillet  87  may allow the bias link  28  to bend relative to the pilot mount  27  to relieve stress therefrom. Similarly, a backside  88  of the bias link  28  may carry a high stress flowing down into the pilot support  41  as suggested in  FIG. 11 . The high stress of the backside  88  may be due to the elastic deformation of the bias link  28  during expansion and contraction of the windage shield  117  during operation of the gas turbine engine  100 . The pilot support  41  and channel  43  may allow the pilot anchor  29  to bend relative to the bias link  28  relieving stress from the pilot anchor  29 . The pilot anchor  29  carries a high stress due to being forced against the pilot receiver  34  to align the windage shield  117  with the fan disk  113 . However, this is a benefit as the stress placed on the pilot anchor  29  is not transmitted to the pilot mount  27  and other parts of the windage shield  117 . 
     A variety of pilot unit configurations may be used to obtain the benefits described herein as suggested in  FIGS. 12-17 . In one embodiment of a pilot unit  226 , a bias link  228  may include a substantially straight section  297  coupled to a pilot mount  227  and a curved section  299  coupled to the substantially straight section  297  as suggested in  FIG. 12 . A second end  283  of the bias link  228  may be coupled to the pilot anchor  229  and an inner tab  223  may be coupled to the pilot anchor  229  with a pilot support  241  coupled between the second end  283  of the bias link  228  and the inner tab  223 . In the illustrative embodiment, no channel is formed between the bias link  228  and inner tab  223 . The pilot unit  226  may further include an outer tab  221  coupled to the pilot mount  227 . 
     In another embodiment of a pilot unit  326 , a bias link  328  may be curved and have a first end  381  coupled to a pilot mount  327  and a second end  383  coupled to a pilot anchor  329  as suggested in  FIG. 13 . An inner tab  323  may be coupled to the pilot anchor  329  and the second end  383  of the bias link  328  may be coupled to both the pilot anchor  329  and inner tab  323 . In the illustrative embodiment, no pilot support is used and no channel is formed between the bias link  328  and inner tab  323 . The pilot unit  326  may further include an outer tab  321  coupled to the pilot mount  327 . 
     In another embodiment of a pilot unit  426 , a bias link  428  may be curved and have a first end  481  coupled to a pilot mount  427  and a second end  483  coupled to a pilot anchor  429  as suggested in  FIG. 14 . An inner tab  423  may be coupled to the pilot anchor  429  with a pilot support  441  coupled between the second end  483  of the bias link  428  and the inner tab  423 . In the illustrative embodiment, no channel is formed between the bias link  428  and inner tab  423  and no outer tab is included. 
     In another embodiment of a pilot unit  526 , a bias link  528  may be curved and have a first end  581  coupled to a pilot mount  527  and a second end  583  coupled to a pilot anchor  529  adjacent a contact surface  571  as suggested in  FIG. 15 . An inner tab  523  may be coupled to the pilot anchor  529  and a pilot support  541  may be coupled between the second end  583  of the bias link  528  and the pilot anchor  529 . In the illustrative embodiment, a channel  543  is formed between the bias link  528  and inner tab  523  and no outer tab is included. A pilot unit  626  is substantially similar to the pilot unit  526  except that the pilot unit  626  includes an outer tab  621  as suggested in  FIG. 16 . 
     In another embodiment of a pilot unit  726 , a bias link  728  may be curved and have a first end  781  coupled to a pilot mount  727  and a second end  783  coupled to a pilot anchor  729  adjacent a contact surface  771  as suggested in  FIG. 17 . An inner tab  723  may be coupled to the pilot anchor  729  with a pilot support  741  coupled between the second end  783  of the bias link  728  and the inner tab  723 . In the illustrative embodiment, a channel  743  is formed between the bias link  428  and inner tab  423  and no outer tab is included. 
     An alternative arrangement for coupling a windage shield  817  to a fan disk  813  in a fan assembly  830  is shown in  FIG. 18 . In the illustrative embodiment, a component anchor  810  includes a fastener  812 , a washer  814 , and a fastener retainer  818 . The component anchor  810  is installed through an anchor-receiving passageway  872  of the windage shield  817  and a flange  832  of the fan disk  813  such that the fastener  812  engages the fastener retainer  818  to force the washer  814  against a pilot mount  827  of the windage shield  817 . 
     In the illustrative embodiment, the component anchor  810  positions the windage shield  817  relative to the fan disk  813  such that the pilot mount  827  of the windage shield  817  contacts a radially extending wall  836  of the fan disk  813  as suggested in  FIG. 18 . A pilot unit  826  of the windage shield  817  includes the pilot mount  827  coupled to a support wall  824  of the windage shield  817 , a bias link  828  coupled to the pilot mount  827  and extending radially inward from the pilot mount  827 , and a pilot anchor  829  coupled to the bias link  828 . The bias link  828  may elastically deform during installation of the component anchor  810  to force the pilot anchor  829  against a pilot receiver  834  of the fan disk  813  with a force F R1  and against the radially extending wall  836  of the fan disk  113  with a force F A3 . The bias link  828  maintains the pilot anchor  829  at a substantially constant distance W from the component anchor  810  during operation of the gas turbine engine  100 . 
     The bias link  828  includes a first end  881  coupled to the pilot mount  827  and a second end  883  coupled to the pilot anchor  829  as suggested in  FIG. 18 . The bias link  828  assumes a generally curved shape with the curve extending away from the fan disk  813 . However, any other suitable shape may be used. The bias link  828  may cooperate with the pilot anchor  829  to maintain the pilot anchor  829  in contact with a radially extending wall  836  and pilot receiver  834  of the fan disk  813  as suggested in  FIG. 21 . The anchor  810  couples the windage shield  817  to the fan disk  813  and the bias link  828  maintains a constant deflection of the pilot anchor  829  relative to the fan disk  813  during operation of the gas turbine engine  100 . This applies similarly to the pilot units  26 - 726  and component anchor  10  described above. 
     Contact between the pilot mount  827  and fan disk  813  may affect stress distribution between the components due to the sliding interface between the pilot mount  827  and wall  836  as suggested in  FIG. 20 . A low coefficient of friction allows a fillet  887  and backside  888  of the pilot unit  826  to carry more stress than the flange  832  of the fan disk  813 . The stress transfers from the fillet  887  and backside  888  to the flange  832  as the coefficient of friction increases. Additional stress is also added to the fillet  887  and backside  888  as the coefficient of friction increases. However, these stresses are relatively lower than stresses formed in a reference pilot unit which does not incorporate the features of the pilot units  26 - 826  as suggested in  FIG. 19 . 
     SECOND ASPECT OF THE DISCLOSURE 
     In one illustrative embodiment, the one or more component anchors  10  include a fastener  12 , a washer  14 , a bushing  16 , and a fastener retainer  18  as shown in  FIG. 5 . The component anchor  10  is installed along an installation axis  150  through the windage shield  117  and the fan disk  113 . The fastener  12  includes a head  52  and a shaft  54  coupled to the head  52 . The shaft  54  includes a substantially smooth neck section  58  and an engagement section  56  arranged to couple the fastener  12  to the fastener retainer  18 . In the illustrative embodiment, the engagement section  56  and fastener retainer  18  are threaded. However, it should be noted that other arrangements for coupling the fastener  12  with the fastener retainer  18  are contemplated, such as a key, pin, spring clip, or other suitable alternative. 
     The washer  14  includes an annular body  62  and a fastener-receiving aperture  64  formed through the annular body  62  as shown in  FIG. 5 . The annular body  62  includes an engagement surface  66  and a retainer surface  68 . The engagement surface  66  is arranged to contact the bushing  16  and the pilot mount  27  of the windage shield  117 . The retainer surface  68  is arranged to contact the head  52  of the fastener  12  to force the washer  14  against the bushing  16  and pilot mount  27 . The pilot mount  27  includes an anchor-receiving passageway  72  formed through the pilot mount  27 . The washer  14  has a larger outer diameter than the anchor-receiving passageway  72  such that the washer  14  does not pass through the anchor-receiving passageway  72 . 
     The bushing  16  includes a sleeve  82  and a flange  84  coupled to one end of the sleeve  82  as shown in  FIG. 5 . The sleeve  82  has a smaller diameter than the anchor-receiving passageway  72  such that the sleeve  82  may pass through the anchor-receiving passageway  72  to contact the washer  14 . A length of the bushing  16  is generally longer than the length of the anchor-receiving passageway  72 . For example, the sleeve  82  may extend through the anchor-receiving passageway  72  to contact the washer  14  on one side of the pilot mount  27  while the flange  84  contacts the fan disk  113  on an opposing side of the pilot mount  27  as shown in  FIG. 8 . The pilot mount  27  further include a recess  74  formed at one end of the anchor-receiving passageway  72 . The recess  74  may be sized and arranged to surround the flange  84  of the bushing  16 . 
     The fastener retainer  18  includes an annular retainer body  92  and an inner engagement surface  94  as shown in  FIG. 5 . The inner engagement surface  94  may be arranged to couple with the engagement section  56  of the fastener  12 . The annular retainer body  92  is sized and arranged to contact the flange  32  of the fan disk  113  such that the retainer body  92  does not pass through an aperture  38  formed in the flange  32 . In an alternative embodiment, the fastener  12  may be coupled directly to the flange  32  of the fan disk  113  without the use of the fastener retainer  18 . 
     The windage shield  117  may be coupled to the fan disk  113  by assembling the component anchor  10  as suggested in  FIGS. 5-8 . The windage shield  117  is aligned with the fan disk  113  such that the aperture  38  of the fan disk  113  and the anchor-receiving passageway  72  of the windage shield  117  are aligned along the installation axis  150 . The fastener  12  passes along the installation axis  150  through the washer  14 , the anchor-receiving passageway  72  of the windage shield  117 , the bushing  16 , and flange  32  of the fan disk  113  to engage the fastener retainer  18 . 
     The fastener  12 , washer  14 , and bushing  16  may be installed relative to the windage shield  117  in several different orders without departing from the benefits described herein. For example, the bushing  16  may be aligned with the anchor-receiving passageway  72  prior to the fastener  12  passing through the anchor-receiving passageway  72 . In another example, the fastener  12 , washer  14 , and bushing  16  may be aligned relative to the anchor-receiving passageway  72  prior to the windage shield  117  being aligned with the fan disk  113 . 
     The fastener  12  engages the fastener retainer  18  to force the washer  14  against the pilot mount  27  of the windage shield  117  as suggested in  FIG. 6 . In the illustrative embodiment, the component anchor  10  positions the windage shield  117  relative to the fan disk  113  such that the pilot mount  27  of the windage shield  117  is spaced apart from the radially extending wall  36  of the fan disk  113  at a distance A 1  prior to the fastener  12  being tightened. Distance A 1  is also called gap A 1 . At the same time, the washer  14  is spaced apart from the bushing  16  at a corresponding distance B 1 , also called gap B 1 . The distances A 1  and B 1  decrease at a substantially similar rate as the fastener  12  is tightened relative to the fastener retainer  18  as suggested in  FIG. 7 . For example, distance A 1  decreases to a distance A 2  as the fastener  12  is tightened and the distance B 1  decreases by substantially the same amount to a distance B 2 . Additional tightening of the fastener  12  forces the washer  14  to contact the bushing  16  which forces the bushing  16  against the fan disk  113  to move the windage shield  117  to a distance A 3  from the fan disk  113  as suggested by  FIG. 8 . The fastener  12  may then be further tightened to an operating tension to retain the windage shield  117  on the fan disk  112  during operation of the gas turbine engine  100 . In one embodiment, the washer  14  and bushing  16  are formed as a monolithic component where the bushing  16  is spaced at distances B 1 , B 2  from the fan disk  113  during installation of the component anchor. 
     The component anchor  10  couples the windage shield  117  to the fan disk  113  while maintaining a substantially constant axial load on the windage shield  117  as suggested in  FIG. 22 . Position  1  of the chart in  FIG. 22  generally corresponds to the arrangement shown in  FIG. 6 . In this arrangement, the component anchor  10 , anchor-receiving passageway  72 , and aperture  38  are aligned along the installation axis  150  and the component anchor  10  has not placed an axial load on the windage shield  117  relative to the fan disk  113 . 
     Position  2  of the chart in  FIG. 22  generally corresponds to the arrangement shown in  FIG. 7 . In this arrangement, the fastener  12  has been tightened to place an axial load on the fastener  12  and a corresponding axial load on the windage shield  117  to maintain alignment of the windage shield  117  with the fan disk  113 . 
     Position  3  of the chart in  FIG. 22  generally corresponds to the arrangement shown in  FIG. 8 . In this arrangement, the washer  14  has contacted the bushing  16  and the fastener  12  has been tightened to the operating tension to retain the windage shield  117  on the fan disk  112  during operation of the gas turbine engine  100 . The added tension of the fastener  12  is placed on the bushing  16  instead of the windage shield  117  due to the distance A 3  between the windage shield  117  and fan disk  113 . As such, the axial load placed on the windage shield  117  is relatively low compared to the loads placed on the fastener  12  and bushing  16 . The combined axial load placed on the bushing  16  and windage shield  117  is substantially equal to the tension in the fastener  12  as suggested in  FIG. 22 . 
     The component anchor  10  is sized to allow for radial expansion and contraction of the windage shield  117  during operation of the gas turbine engine  100  as suggested in  FIGS. 8-10 . A radially inner gap C 1  and a radially outer gap D 1  are formed between the sleeve  82  and the anchor-receiving passageway  72  when the component anchor  10  is assembled and the windage shield  117  is coupled to the fan disk  113  as shown in  FIG. 8 . 
     In the illustrative embodiment, the gaps C 1  and D 1  are substantially the same size when the temperature and rotational speed of the windage shield  117  are low, for example, prior to operation of the engine  100 . The gaps C 1  and D 1  allow for the windage shield  117  to be coupled to the fan disk  113  without placing additional radial load on the fastener  12  of the component anchor  10 . 
     The fan disk  113  may radially expand during operation of the gas turbine engine  100  increasing the size of gap C 1  to a gap C 2  and decreasing the size of gap D 1  to a gap D 2  as suggested in  FIG. 9 . The fan disk  113  may expand due to increased rotational speed and/or temperature. A relative expansion between the fan disk  113  and windage shield  117  may occur. For example, the fan disk  113  may be made of titanium while the windage shield  117  is made of aluminum. The difference in the coefficients of thermal expansion and modulus of elasticity between the materials may cause the fan disk  113  to expand further or more rapidly than the windage shield  117 . For example, the weight of the fan blades  115  attached to the fan disk  113  places a greater load on the fan disk  113  than the shield wall  22  and support wall  24  place on the pilot unit  26  of the windage shield  117  forcing the fan disk  113  to expand faster than the windage shield  117 . However, the radial load placed on the fastener  12  of the component anchor  10  remains low because the gap D 2  remains even during operation of the engine  100  as suggested in  FIG. 9 . 
     The fan disk  113  may radially contract during run down of the gas turbine engine  100  decreasing the size of gap C 2  to a gap C 3  and increasing the size of gap D 2  to a gap D 3  as suggested in  FIG. 10 . The fan disk  113  may contract due to reduced rotational speed and temperature. A relative contraction between the fan disk  113  and windage shield  117  may occur. For example, the fan disk  113  may be made of titanium while the windage shield  117  is made of aluminum. The difference in the coefficients of thermal expansion and modulus of elasticity between the materials may cause the fan disk  113  to contract further or more rapidly than the windage shield  117 . For example, the windage shield  117  may remain in a hot and expanded state longer than the fan disk  113 . However, the radial load placed on the fastener  12  of the component anchor  10  remains low because the gap C 3  remains even during run down of the engine  100 . 
     The relative expansion and contraction of the windage shield  117  in relation to the fan disk  113  causes a corresponding movement of the windage shield  117  relative to the component anchor  10  as suggested in  FIGS. 9 and 10 . This relative movement may cause fretting to occur and damage the windage shield  117 . However, the component anchor  10  minimizes the amount of fretting due to the limited contact between the components. For example, the component anchor  10  allows for the windage shield  117  to be spaced apart from the fan disk  113  by the distance A 3  during operation of the engine  100  as detailed above. This minimizes contact between the windage shield  117  and fan disk  113  and minimizes fretting. In another example, the washer  14  provides limited contact with the windage shield  117  to retain the windage shield  117  on the fan disk  113  while reducing fretting. 
     The component anchor  10  minimizes radial loads placed on the fastener  12  and minimizes axial loads placed on the windage shield  117  as suggested in  FIGS. 22 and 23 . As described above, position  1  of the charts generally corresponds to the arrangement shown in  FIG. 6 . In this arrangement, the component anchor  10 , anchor-receiving passageway  72 , and aperture  38  are aligned along the installation axis  150  such that minimal radial load is placed on the fastener  12 . The pilot anchor  29  of the windage shield  117  is arranged to be press fit with the pilot receiver  34  of the fan disk  113  placing an initial radial load on the windage shield  117  as suggested in  FIG. 23 . The press fit creates a frictional force between the pilot anchor  29  and pilot receiver  34  which provides tangential alignment of the windage shield  117  with the fan disk  113 . 
     Position  2  of the charts in  FIGS. 22 and 23  generally correspond to the arrangement shown in  FIG. 7 . In this arrangement, the fastener  12  has been tightened causing the bias link  28  of the windage shield  117  to elastically deform and further force the pilot anchor  29  against the pilot receiver  34 . The axial load placed on the fastener  12  increases while the radial load placed on the fastener  12  remains low due to the gaps C 1  and D 1  as described above. 
     Position  3  of the charts in  FIGS. 22 and 23  generally correspond to the arrangement shown in  FIG. 8 . In this arrangement, tightening of the fastener  12  increases the axial loads in the fastener  12  and bushing  16  while the radial loads on the fastener  12  and windage shield  117  remain substantially constant. 
     Positions  4 - 6  of the charts in  FIGS. 22 and 23  generally correspond to various operating conditions of the gas turbine engine  100 . Position  4  corresponds to engine conditions during take-off of an aircraft. The gas turbine engine  100  may experience increased loading during take-off placing increased radial loading on the windage shield  117  as suggested in  FIG. 23 . However, the radial loading on the fastener  12  of component anchor  10  remains low as suggested and described above with regard to  FIG. 9 . Axial loading of the windage shield  117  remains substantially constant due to the distance A 3  from the fan disk  113  and ability to move relative to the component anchor  10  as described above and as suggested in  FIG. 22 . Frictional forces between the windage shield  117  and washer  14  may vary the radial loads placed on the fastener  12  during relative expansion between the windage shield  117  and fan disk  113  as described above. 
     Position  5  of the charts in  FIGS. 22 and 23  corresponds to engine conditions during flight. The engine  100  may generally experience decreased loading compared to the take-off conditions while the aircraft is in flight. As such, the radial loading on the windage shield  117  is also decreased as compared to take-off loading. The radial loading on the fastener  12  and axial loading on the windage shield  117  remain substantially constant during flight. 
     Position  6  corresponds to engine conditions during landing of the aircraft and run down of the engine  100 . The gas turbine engine  100  may begin to cool during landing causing the fan disk  113  to contract and the windage shield  117  to experience decreased radial loading. However, the radial loading on the fastener  12  of component anchor  10  remains low as suggested and described above with regard to  FIG. 10 . The axial loading on the windage shield  117  remain substantially constant during landing. 
     THIRD ASPECT OF THE DISCLOSURE 
     Another alternative arrangement for coupling a windage shield  917  to a fan disk  913  in a fan assembly  930  is shown in  FIG. 24 . In the illustrative embodiment, a component anchor  910  includes a fastener  912 , washer  914 , insert  940 , bushing  916 , and fastener retainer  918 . The component anchor  910  is installed along an installation axis  950  through an anchor-receiving passageway  972  of the windage shield  917  and a flange  932  of the fan disk  913 . 
     The fastener  912  includes a head  952  and a shaft  954  coupled to the head  952 . The shaft  954  includes a substantially smooth neck section  958  and an engagement section  956  arranged to couple the fastener  912  to the fastener retainer  918 . In the illustrative embodiment, the engagement section  956  and fastener retainer  918  are threaded. However, it should be noted that other arrangements for coupling the fastener  912  with the fastener retainer  918  are contemplated, such as a key, pin, spring clip, or other suitable alternative. 
     The insert  940  generally includes a tube  942  and a flange  944  coupled to the tube  942  as shown in  FIG. 24 . The tube  942  may be sized to pass into the anchor-receiving passageway  972  of the windage shield  917  and mate with an interior surface of the anchor-receiving passageway  972 . The flange  944  may have a larger outer diameter than the anchor-receiving passageway  972  such that the insert  940  does not pass through the anchor-receiving passageway  972 . The flange  944  is arranged to contact the pilot mount  927  to force the windage shield  917  toward the fan disk  913  as will be described further herein. 
     The washer  914  includes an annular body  962  and a fastener-receiving aperture  964  formed through the annular body  962  as shown in  FIG. 24 . The annular body  962  includes an engagement surface  966  and a retainer surface  968 . The engagement surface  966  is arranged to contact the bushing  916  and the flange  944  of the insert  940 . The retainer surface  968  is arranged to contact the head  952  of the fastener  912  to force the washer  914  against the bushing  916  and insert  940 . The washer  914  has a larger outer diameter than a bushing-receiving passageway  948  of the tube  942  such that the washer  914  does not pass through the insert  940 . 
     The bushing  916  includes a sleeve  982  and a flange  984  coupled to one end of the sleeve  982  as shown in  FIG. 24 . The sleeve  982  has a smaller diameter than the bushing-receiving passageway  948  of the insert  940  such that the sleeve  982  may pass through the insert  940  to contact the washer  914 . A length of the bushing  916  is generally longer than the length of the anchor-receiving passageway  972 . For example, the sleeve  982  may extend through the anchor-receiving passageway  972  to contact the washer  914  on one side of the pilot mount  927  while the flange  984  contacts the fan disk  913  on an opposing side of the pilot mount  927  as shown in  FIG. 24 . The pilot mount  927  further includes a recess  974  formed at one end of the anchor-receiving passageway  972 . The recess  974  may be sized and arranged to surround the flange  984  of the bushing  916 . 
     The fastener retainer  918  generally includes an annular retainer body  992  and an inner engagement surface  994  as shown in  FIG. 24 . As described above, the inner engagement surface  994  may be arranged to couple with the engagement section  956  of the fastener  912 . The annular retainer body  992  is sized and arranged to contact the flange  932  of the fan disk  913  such that the retainer body  992  does not pass through an aperture  938  formed in the flange  932 . In an alternative embodiment, the fastener  912  may be coupled directly to the flange  932  of the fan disk  913  without the use of the fastener retainer  918 . 
     A pilot unit  926  of the windage shield  917  includes the pilot mount  927  coupled to a support wall  924  of the windage shield  917 , a bias link  928  coupled to the pilot mount  927  and extending radially inward from the pilot mount  927 , and a pilot anchor  929  coupled to the bias link  928  as suggested in  FIG. 24 . The bias link  928  may elastically deform during installation of the component anchor  910  to force the pilot anchor  929  against a pilot receiver  934  of the fan disk  913  with a force F R1  and against the radially extending wall  936  of the fan disk  113  with a force F A3  as suggested in  FIG. 25 . The bias link  928  maintains the pilot anchor  929  at a substantially constant distance W from the component anchor  910  during operation of the gas turbine engine  100 . 
     The bias link  928  assumes a generally curved shape with the curve extending away from the fan disk  913  as suggested in  FIG. 25 . However, any other suitable shape may be used. The bias link  928  may cooperate with the pilot anchor  929  to maintain the pilot anchor  929  in contact with a radially extending wall  936  and pilot receiver  934  of the fan disk  913 . The anchor  910  couples the windage shield  917  to the fan disk  913  and the bias link  928  maintains a constant deflection of the pilot anchor  929  relative to the fan disk  913  during operation of the gas turbine engine  100 . 
     The windage shield  917  may be coupled to the fan disk  913  by assembling the component anchor  910  as suggested in  FIG. 25 . The windage shield  917  is aligned with the fan disk  913  such that the aperture  938  of the fan disk  913  and the anchor-receiving passageway  972  of the windage shield  917  are aligned along the installation axis  950 . The fastener  912  passes along the installation axis  950  through the washer  914 , the insert  940 , the anchor-receiving passageway  972  of the windage shield  917 , the bushing  916 , and flange  932  of the fan disk  913  to engage the fastener retainer  918 . 
     The fastener  912 , insert  940 , washer  914 , and bushing  916  may be installed relative to the windage shield  917  in several different orders without departing from the benefits described herein. For example, the bushing  916  may be aligned with the anchor-receiving passageway  972  prior to the fastener  912  passing through the anchor-receiving passageway  972 . In another example, the bushing  916  and insert  940  may be aligned with the anchor-receiving passageway  972  prior to the fastener  912  passing through the anchor-receiving passageway  972 . In yet another example, the fastener  912 , insert  940 , washer  914 , and bushing  916  may be aligned relative to the anchor-receiving passageway  972  prior to the windage shield  917  being aligned with the fan disk  913 . 
     The fastener  912  engages the fastener retainer  918  to hold the windage shield  917  to the fan disk  913  as suggested in  FIG. 25 . The head  952  of the fastener  912  forces the washer  914  against the insert  940 . The washer  914  forces the insert  940  against the pilot mount  927  of the windage shield  917 . The insert  940  may include a groove  946  formed in an outer surface of the tube  942  adjacent to the flange  944 . The groove  946  may allow the flange  944  to mate with the pilot mount  927 . Tightening of the fastener  912  forces the washer  914  to contact the bushing  916  which forces the bushing  916  against the fan disk  913 . The fastener  912  may then be further tightened to an operating tension to retain the windage shield  917  on the fan disk  913  during operation of the gas turbine engine  100 . 
     Similar to component anchor  10 , the component anchor  910  couples the windage shield  917  to the fan disk  913  while maintaining a substantially constant axial load on the windage shield  917  and low radial load on the component anchor  910 . For example, at least some of the tension of the fastener  912  is placed on the bushing  916  instead of the windage shield  917  due to the distance A 3  between the windage shield  917  and fan disk  913  as suggested in  FIG. 25 . In another example, gaps C 1  and D 1  between the tube  942  of the insert  940  and sleeve  982  of the bushing  916  allow the windage shield  917  to expand and contract relative to the fan disk  913  without placing additional radial load on the fastener  912  of the component anchor  910 . 
     Another alternative arrangement for coupling a windage shield  1017  to a fan disk  1013  in a fan assembly  1030  is shown in  FIG. 27 . In the illustrative embodiment, a component anchor  1010  includes a fastener  1012 , a bushing  1016 , and a fastener retainer  1018 . The component anchor  1010  is installed through an anchor-receiving passageway  1072  of the windage shield  1017  and a flange  1032  of the fan disk  1013 . 
     The fastener  1012  includes a head  1052  and a shaft  1054  coupled to the head  1052  as suggested in  FIG. 27 . The shaft  1054  includes a substantially smooth neck section  1058  and an engagement section  1056  arranged to couple the fastener  1012  to the fastener retainer  1018 . In the illustrative embodiment, the engagement section  1056  and fastener retainer  1018  are threaded. However, it should be noted that other arrangements for coupling the fastener  1012  with the fastener retainer  1018  are contemplated, such as a key, pin, spring clip, or other suitable alternative. 
     The bushing  1016  includes a sleeve  1082 , a contact flange  1084  coupled to one end of the sleeve  1082 , and a coupler flange  1089  coupled to an opposing end of the sleeve  1082  as shown in  FIGS. 26 and 27 . The contact flange  1084  and sleeve  1082  have smaller diameters than an anchor-receiving passageway  1072  formed through a pilot mount  1027  of the windage shield  1017  such that the contact flange  1084  and sleeve  1082  may pass through the pilot mount  1027  to contact a flange  1032  of the fan disk  1013  as suggested in  FIG. 27 . The coupler flange  1089  has a larger diameter than the anchor-receiving passageway  1072  and is arranged to contact the pilot mount  1027  to hold the windage shield  1017  on the fan disk  1013 . 
     A pilot unit  1026  of the windage shield  1017  includes the pilot mount  1027  coupled to a support wall  1024  of the windage shield  1017 , a bias link  1028  coupled to the pilot mount  1027  and extending radially inward from the pilot mount  1027 , and a pilot anchor  1029  coupled to the bias link  1028  as suggested in  FIG. 27 . The bias link  1028  may elastically deform during installation of the component anchor  1010  to force the pilot anchor  1029  against a pilot receiver  1034  of the fan disk  1013  with a force F R1  and against the radially extending wall  1036  of the fan disk  113  with a force F A3 . The bias link  1028  maintains the pilot anchor  1029  at a substantially constant distance W from the component anchor  1010  during operation of the gas turbine engine  100 . 
     The bias link  1028  assumes a generally curved shape with the curve extending away from the fan disk  1013  as suggested in  FIG. 27 . However, any other suitable shape may be used. The bias link  1028  may cooperate with the pilot anchor  1029  to maintain the pilot anchor  1029  in contact with a radially extending wall  1036  and pilot receiver  1034  of the fan disk  1013 . The anchor  1010  couples the windage shield  1017  to the fan disk  1013  and the bias link  1028  maintains a constant deflection of the pilot anchor  1029  relative to the fan disk  1013  during operation of the gas turbine engine  100 . 
     The fastener  1012  engages the fastener retainer  1018  to hold the windage shield  1017  to the fan disk  1013  as suggested in  FIG. 27 . The head  1052  of the fastener  1012  forces the coupler flange  1089  against the pilot mount  1027  of the windage shield  1017 . Tightening of the fastener  1012  forces the contact flange  1084  of the bushing  1016  against the fan disk  1013 . The fastener  1012  may then be further tightened to an operating tension to retain the windage shield  1017  on the fan disk  1013  during operation of the gas turbine engine  100 . 
     Similar to component anchor  10 , the component anchor  1010  couples the windage shield  1017  to the fan disk  1013  while maintaining a substantially constant axial load on the windage shield  1017  and low radial load on the component anchor  1010 . For example, at least some of the tension of the fastener  1012  is placed on the bushing  1016  instead of the windage shield  1017  due to the distance A 3  between the windage shield  1017  and fan disk  1013  as suggested in  FIG. 27 . In another example, gaps C 1  and D 1  between the anchor-receiving passageway  1072  and sleeve  1082  of the bushing  1016  allow the windage shield  1017  to expand and contract relative to the fan disk  1013  without placing additional radial load on the fastener  1012  of the component anchor  1010 . In some embodiments, an insert, similar to insert  940  shown in  FIGS. 24 and 25 , may be used with component anchor  1010 . 
     Another alternative arrangement for coupling a windage shield  1117  to a fan disk  1113  in a fan assembly  1130  is shown in  FIG. 29 . In the illustrative embodiment, a component anchor  1110  includes a fastener  1112  and a fastener retainer  1118 . The component anchor  1110  is installed through the windage shield  1117  and fan disk  1113 . The fastener  1112  includes a barrel section  1182 , a head  1152  coupled to one end of the barrel section  1182 , and an engagement section  1156  coupled to an opposing end of the barrel section  1182  as shown in  FIGS. 28 and 29 . The engagement section  1156  is arranged to couple the fastener  1112  to the fastener retainer  1118 . In the illustrative embodiment, the engagement section  1156  and fastener retainer  1118  are threaded. However, it should be noted that other arrangements for coupling the fastener  1112  with the fastener retainer  1118  are contemplated, such as a key, pin, spring clip, or other suitable alternative. 
     The fastener  1112  further includes a contact flange  1184  coupled to the barrel section  1182  and a coupler flange  1189  coupled to the barrel section  1182  and spaced apart from the contact flange  1184  as shown in  FIGS. 28 and 29 . The contact flange  1184  and barrel section  1182  have smaller diameters than an anchor-receiving passageway  1172  formed through a pilot mount  1127  of the windage shield  1117  such that the contact flange  1184  and barrel section  1182  may pass through the pilot mount  1127  to contact a flange  1132  of the fan disk  1113  as suggested in  FIG. 29 . The coupler flange  1189  has a larger diameter than the anchor-receiving passageway  1172  and is arranged to contact the pilot mount  1127  to hold the windage shield  1117  on the fan disk  1113 . 
     A pilot unit  1126  of the windage shield  1117  includes the pilot mount  1127  coupled to a support wall  1124  of the windage shield  1117 , a bias link  1128  coupled to the pilot mount  1127  and extending radially inward from the pilot mount  1127 , and a pilot anchor  1129  coupled to the bias link  1128  as suggested in  FIG. 29 . The bias link  1128  may elastically deform during installation of the component anchor  1110  to force the pilot anchor  1129  against a pilot receiver  1134  of the fan disk  1113  with a force F R1  and against the radially extending wall  1136  of the fan disk  113  with a force F A3 . The bias link  1128  maintains the pilot anchor  1129  at a substantially constant distance W from the component anchor  1110  during operation of the gas turbine engine  100 . 
     The bias link  1028  assumes a generally curved shape with the curve extending away from the fan disk  1013  as suggested in  FIG. 29 . However, any other suitable shape may be used. The bias link  1028  may cooperate with the pilot anchor  1029  to maintain the pilot anchor  1029  in contact with a radially extending wall  1036  and pilot receiver  1034  of the fan disk  1013 . The anchor  1010  couples the windage shield  1017  to the fan disk  1013  and the bias link  1028  maintains a constant deflection of the pilot anchor  1029  relative to the fan disk  1013  during operation of the gas turbine engine  100 . 
     The fastener  1112  engages the fastener retainer  1118  to hold the windage shield  1117  to the fan disk  1113  as suggested in  FIG. 29 . The head  1152  of the fastener  1112  forces the coupler flange  1189  against the pilot mount  1127  of the windage shield  1117 . Tightening of the fastener  1112  forces the contact flange  1184  of the fastener  1112  against the fan disk  1113 . The fastener  1112  may then be further tightened to an operating tension to retain the windage shield  1117  on the fan disk  1113  during operation of the gas turbine engine  100 . 
     Similar to component anchor  10 , the component anchor  1110  couples the windage shield  1117  to the fan disk  1113  while maintaining a substantially constant axial load on the windage shield  1117  and low radial load on the component anchor  1110 . For example, at least some of the tension of the fastener  1112  is placed on the fastener  1112  instead of the windage shield  1117  due to the distance A 3  between the windage shield  1117  and fan disk  1113  as suggested in  FIG. 29 . In another example, gaps C 1  and D 1  between the anchor-receiving passageway  1172  and barrel section  1182  of the fastener  1112  allow the windage shield  1117  to expand and contract relative to the fan disk  1113  without placing additional radial load on the fastener  1112  of the component anchor  1110 . In some embodiments, an insert, similar to insert  940  shown in  FIGS. 24 and 25 , may be used with component anchor  1110 .