the engine operating range combustor 30 has a natural acoustic operating range middle dome heat shield endbodies 120 and 122 facilitate providing additional structural support to middle dome 56 specifically because heat shield endbodies 120 and 122 have a shorted winglength 126 and 128 than outer dome and inner dome endbodies 106 and 140 respectively middle dome endbodies 120 and 122 facilitate increasing a stiffness of middle dome heat shield 102 such that the natural frequency of middle dome heat shield 102 is increased above that of the combustor natural acoustic operating range without adversely impacting engine operability more specifically the shortened winglength 126 and 128 does not adversely impact nox and or co emissions but does facilitate reducing vibrational stresses that may be induced to middle dome 56 as such middle dome endbodies 120 and facilitate extending a useful life of combustor 30 the above described combustor system for a gas turbine engine is cost effective and reliable the combustor system includes a combustor including a heat shield that includes at least one endbody that has a shortend winglength in comparison to the other heatshield endbodies the shortened winglength facilitates reducing vibrational stresses that may be induced to the dome assembly by increasing the natural frequency of the endbody above that of the combustor acoustic operating range but without adversely affecting engine operability as a result the endbody facilitates extending a useful life of the combustor in cost effective and reliable manner exemplary embodiments of combustor assemblies are described above in detail the systems are not limited to the specific embodiments described herein but rather components of each.