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A diffuser system for a compressor for a gas turbine engine, the compressor having an impeller and the gas turbine engine having a combustor and a fuel injector proximate to the combustor, includes a first diffuser and a second diffuser. The first diffuser is configured to receive compressed air fro

A diffuser system for a compressor for a gas turbine engine, the compressor having an impeller and the gas turbine engine having a combustor and a fuel injector proximate to the combustor, includes a first diffuser and a second diffuser. The first diffuser is configured to receive compressed air from the impeller. The second diffuser is coupled to receive the compressed air from the first diffuser. The second diffuser comprises a housing comprising a first wall and a second wall. The first and second walls form a diffuser flow passage therebetween. The first wall or the second wall, or both, further form an opening through the first and second walls for the fuel injector to pass through when removed from the combustor.

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1. 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

1. 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; anda 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. 2. The diffuser system of claim 1, wherein the first wall and the second wall form the outlet for the diffuser flow passage for the compressed air to flow through toward the combustor, and the opening is formed also through at least a portion of the outlet. 3. The diffuser system of claim 1, wherein the opening is formed through both the first and second walls. 4. The diffuser system of claim 1, wherein: the first wall comprises a first region and a second region, the second region being connected to the first region;the second wall comprises a third region and a fourth region, the fourth region being connected to the third region;the first wall and the second wall form the diffuser flow passage between the first region and the third region; andthe plurality of de-swirl vanes are housed between the second region and the fourth region. 5. The diffuser system of claim 1, wherein the gas turbine engine further includes a plurality of additional fuel injectors proximate the combustor, and the first wall or the second wall, or both, further form a plurality of additional openings therethrough for the plurality of additional fuel injectors to pass through when removed from the combustor. 6. The diffuser system of claim 1, wherein: the first diffuser is a radial diffuser; andthe second diffuser is an axial diffuser. 7. The diffuser system of claim 1, wherein the first diffuser and the second diffuser are both formed integral to the compressor. 8. The diffuser system of claim 1, wherein the opening is disposed upstream of the outlet in which the air is deposited to the combustor. 9. The diffuser system of claim 1, wherein the first wall and the second wall are separate from the inner wall and the outer wall of the combustor. 10. The diffuser system of claim 1, wherein the combustor includes a combustor casing and the inner and outer walls, and the first wall and the second wall are independent from the combustor casing and the inner and outer walls of the combustor. 11. A compressor for a 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 thereto, the compressor comprising: a housing;an impeller rotationally mounted within the housing and configured to supply compressed air;a first diffuser formed within the housing and configured to receive the compressed air from the impeller; anda second diffuser formed within the housing and coupled to receive the compressed air from the first diffuser and supply the compressed air to the combustor, the second diffuser formed at least in part by a first wall and a second wall of the housing, the first wall and second wall with a trailing edge forming a diffuser flow passage of the second diffuser between the first and second walls 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; anda 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. 12. The compressor of claim 11, wherein the first wall and the second wall form the outlet for the diffuser flow passage proximate the end wall cover for the compressed air to flow through toward the combustor, and the opening is formed also through at least a portion of the outlet. 13. The compressor of claim 12, wherein the opening is formed through both the first and second walls. 14. The compressor of claim 11, wherein: the first wall comprises a first region and a second region, the second region connected to the first region;the second wall comprises a third region and a fourth region, the fourth region connected to the third region;the first wall and the second wall form the diffuser flow passage between the first region and the third region; andthe plurality of de-swirl vanes are housed between the second region and the fourth region. 15. A gas turbine engine, comprising: a housing;a turbine formed within the housing and configured to receive a combustion gas and operable, upon receipt thereof, to supply a first drive force;a combustor formed within the housing and configured to receive compressed air and fuel and operable, upon receipt thereof, to supply the combustion gas to the turbine, the combustor having an inner wall, an outer wall, and an end wall cover upstream of the inner and outer walls;a fuel injector coupled to the combustor and configured to supply the fuel thereto; anda compressor formed within the housing and configured to supply the compressed air to the combustor, the compressor comprising: an impeller rotationally mounted within the housing and configured to supply the compressed air;a first diffuser formed within the housing and configured to receive the compressed air from the impeller;a second diffuser formed within the housing and coupled to receive the compressed air from the first diffuser and supply the compressed air to the combustor, the second diffuser formed at least in part by a first wall and a second wall of the housing, the first wall and second walls with a trailing edge forming a diffuser flow passage of the second diffuser between the first and second walls 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, the opening disposed within the diffuser flow passage, the fuel injector to pass through the opening to supply fuel to the combustor; anda deswirl section coupled between the first diffuser and the second diffuser, the deswirl section connected to the first diffuser and the second diffuser and 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. 16. The gas turbine engine of claim 15, wherein the first wall and the second wall form the outlet for the diffuser flow passage proximate the end wall cover for the compressed air to flow through toward the combustor, and the opening is formed also through at least a portion of the outlet. 17. The gas turbine engine of claim 15, wherein the opening is formed through both the first and second walls. 18. The gas turbine engine of claim 15, wherein: the first wall comprises a first region and a second region, the second region connected to the first region;the second wall comprises a third region and a fourth region, the fourth region connected to the third region;the first wall and the second wall form the diffuser flow passage between the first region and the third region; andthe plurality of de-swirl vanes are housed between the second region and the fourth region. 19. The gas turbine engine of claim 15, wherein: the first diffuser is a radial diffuser; andthe second diffuser is an axial diffuser.