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A combustor liner including a dome section having a positioning hole defined at a first radial distance and sized to receive a first heat shield fastener to at least substantially prevent radial and circumferential motion of the first fastener, a circumferential slot sized to receive a second heat s

A combustor liner including a dome section having a positioning hole defined at a first radial distance and sized to receive a first heat shield fastener to at least substantially prevent radial and circumferential motion of the first fastener, a circumferential slot sized to receive a second heat shield fastener to at least substantially prevent radial motion of the second fastener while allowing limited circumferential motion of the second fastener, and a clearance hole defined at a second radial distance and sized to receive a third heat shield fastener to allow limited radial and circumferential motion of the third fastener.

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What is claimed is: 1. A combustor liner for a gas turbine engine, the liner being adapted to retain a plurality of heat shield portions each including at least first, second and third protruding fasteners, the combustor liner comprising a dome section having for each heat shield portion a position

What is claimed is: 1. A combustor liner for a gas turbine engine, the liner being adapted to retain a plurality of heat shield portions each including at least first, second and third protruding fasteners, the combustor liner comprising a dome section having for each heat shield portion a positioning hole defined at a first radial distance from a central axis of the liner, the positioning hole being sized to receive the first fastener to at least substantially prevent radial and circumferential motion of the first fastener within the positioning hole, a circumferential slot extending circumferentially with respect to the central axis, the circumferential slot being sized to receive the second fastener to at least substantially prevent radial motion of the second fastener within the slot while allowing limited circumferential motion of the second fastener within the slot, and a clearance hole defined at a second radial distance from the central axis, the clearance hole being sized to receive the third fastener to allow limited radial and circumferential motion of the third fastener within the clearance hole, the limited circumferential motion of the second fastener within the slot and the limited radial and circumferential motion of the third fastener within the clearance hole accommodating a difference in thermal expansion between the dome section and each of the heat shield portions. 2. The combustor liner as defined in claim 1, wherein the circumferential slot extends circumferentially at the first radial distance from the central axis. 3. The combustor liner as defined in claim 1, wherein the positioning hole is sized to completely prevent radial and circumferential motion of the first fastener within the positioning hole. 4. The combustor liner as defined in claim 1, wherein the circumferential slot is sized to completely prevent radial motion of the second fastener within the slot. 5. The combustor as defined in claim 1, wherein the first radial distance is smaller than the second radial distance. 6. The combustor as defined in claim 1, wherein the dome section has for each heat shield portion an additional clearance hole defined at the second radial distance from the central axis and sized to receive a fourth fastener of the heat shield portion to allow limited radial and circumferential motion of the fourth fastener within the additional clearance hole. 7. A combustor liner for a gas turbine engine, the liner comprising an annular dome section interconnecting annular inner and outer walls of the liner, the dome section having a plurality of openings defined therethrough sized to each receive a fuel nozzle, the dome section also having a circular positioning hole, a circumferential slot and at least one clearance hole defined therethrough in proximity of each of the openings for receiving a respective fastener of a heat shield surrounding the fuel nozzle, the circular positioning hole having a first diameter, the circumferential slot extending circumferentially with respect to a central axis of the liner and having a radially defined width corresponding to the first diameter and a circumferentially defined length larger than the width, and the at least one clearance hole being larger than the circular positioning hole and being defined at a different radial distance than that of the positioning hole with respect to the central axis. 8. The combustor liner as defined in claim 7, wherein the circumferential slot extends at a same radial distance than that of the positioning hole with respect to a central axis of the liner. 9. The combustor liner as defined in claim 7, wherein the circular positioning hole and the circumferential slot are defined in proximity of the inner wall, and the at least one clearance hole is defined in proximity of the outer wall. 10. The combustor liner as defined in claim 7, wherein the at least one clearance hole is circular and has a second diameter larger than the first diameter. 11. The combustor liner as defined in claim 7, wherein the at least one clearance hole includes two clearances holes defined at a same radial distance with respect to the central axis and circumferentially spaced apart from one another. 12. A combustor liner for a gas turbine engine, the combustor liner including an annular inner wall, and annular outer wall, and a radially extending dome section interconnecting the inner and outer walls, the dome section including means for retaining a first element of a heat shield at a first radial distance from a central axis of the liner while at least substantially preventing relative radial and circumferential motion between the first element and the dome section, means for retaining a second element of the heat shield while at least substantially preventing relative radial motion between the second element and the dome section and allowing a predetermined amount of relative circumferential motion between the second element and the dome section, and means for retaining a third element of the heat shield at a second radial distance from the central axis of the combustor while allowing a predetermined amount of relative radial and circumferential motion between the third element and the dome section. 13. The combustor liner as defined in claim 12, wherein the means for retaining the second element of the heat shield retain the second element at the first radial distance from the central axis. 14. The combustor liner as defined in claim 12, wherein the means for retaining the first element include a circular positioning hole defined in the dome section at the first radial distance from the central axis. 15. The combustor liner as defined in claim 12, wherein the means for retaining the second element include a circumferential slot extending circumferentially at the first radial distance from the central axis. 16. The combustor liner as defined in claim 15, wherein the means for retaining the first element include a circular positioning hole defined in the dome section at the first radial distance from the central axis, and the circumferential slot has a radially defined width corresponding to a diameter of the circular positioning hole. 17. The combustor liner as defined in claim 14, wherein the means for retaining the third element include a circular clearance hole having a diameter larger than that of the circular positioning hole. 18. The combustor liner as defined in claim 12, wherein the means for retaining the first and second elements are defined in proximity of the inner wall, and the means for retaining the third element are defined in proximity of the outer wall. 19. A method of accommodating relative thermal deflections between a heat shield and a dome section of a combustor for a gas turbine engine, the heat shield being connected to the dome section by at least first, second and third fasteners having a fixed position with respect to the heat shield, the first and third fasteners being engaged to the dome section at a different radial distances from a central axis of the dome section, the method comprising: at least substantially preventing relative radial and circumferential motion between the first fastener and the dome section; at least substantially preventing relative radial motion between the second fastener and the dome section while allowing a limited relative circumferential motion between the second fastener and the dome section; and allowing a limited relative radial and circumferential motion between the third fastener and the dome section. 20. The method according to claim 19, wherein the heat shield is also connected to the dome section by a fourth fastener engaged to the dome section at the second distance from the central axis of the dome section, and the method further comprises allowing limited relative radial and circumferential motion between the fourth fastener and the dome section. 21. The method according to claim 19, wherein the relative radial and circumferential motion between the first fastener and the dome section is completely prevented. 22. The method according to claim 19, wherein the relative radial motion between the second fastener and the dome section is completely prevented.