Abstract: Composite patching has been proven to be an efficient and economical method to repair damaged aircraft components.The significant difference in thermal expansion coefficients between the composite patch and the metallic substrate would introduce thermal residual stresses in the components.Research achievements of the thermal residual stresses in composite repairs of metallic components are reviewed,including some widely used models to predict thermal residual stresses,influences of restraint by the surrounding structure and curing cycles on the thermal residual stresses,and methods to minimize the residual stresses.Some recommendations for future work are also presented.