Patent ID: 8438854

Claim:
A diffuser system for a compressor for a gas turbine engine, the compressor having an impeller and the gas turbine engine having a combustor with an inner wall, an outer wall, and an end wall cover upstream of the inner and outer walls and a fuel injector proximate to the combustor, the diffuser system comprising: a first diffuser configured to receive compressed air from the impeller; a second diffuser coupled to receive the compressed air from the first diffuser and supply the compressed air to the combustor, the second diffuser comprising a housing comprising a first wall and a second wall having a trailing edge, the first and second walls forming a diffuser flow passage therebetween and an outlet at the trailing edge of the second wall, the first wall and the second wall being separated by a varying distance that increases along a direction of flow within the diffuser flow passage, the first wall or the second wall, or both, forming an opening through the first and second walls and disposed within the diffuser flow passage, the fuel injector to pass through the opening to supply fuel to the combustor; and a deswirl section coupled between the first diffuser and the second diffuser, the deswirl section connected to the first diffuser and the second diffuser, the deswirl section comprising a plurality of de-swirl vanes formed within the housing and configured to deswirl the compressed air as it flows between the first diffuser and the second diffuser.