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A diffuser for use in a gas turbine engine, the diffuser having a first wall, a second wall, and a flow separator. The first and second wall define an annular cavity, with the annular cavity having an inlet. The first and second wall also forming a prediffuser that is proximate the inlet, and a dump

A diffuser for use in a gas turbine engine, the diffuser having a first wall, a second wall, and a flow separator. The first and second wall define an annular cavity, with the annular cavity having an inlet. The first and second wall also forming a prediffuser that is proximate the inlet, and a dump region distal the inlet. The flow separator extends from the first wall into the annular cavity.

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1. A diffuser for use in a gas turbine engine, the diffuser comprising: a first prediffuser wall;a second prediffuser wall, the first prediffuser wall and the second prediffuser wall defining an annular cavity having an inlet and an outlet and defining an annular prediffuser airflow path from the in

1. A diffuser for use in a gas turbine engine, the diffuser comprising: a first prediffuser wall;a second prediffuser wall, the first prediffuser wall and the second prediffuser wall defining an annular cavity having an inlet and an outlet and defining an annular prediffuser airflow path from the inlet to the outlet, the first prediffuser wall and the second prediffuser wall diverging from the inlet to the outlet forming a prediffuser, the first prediffuser wall diverging in a downstream direction at a first angle relative to a diffuser center axis;a dump region having a first dump region wall and a second dump region wall;the first dump region wall extending from the first prediffuser wall at the outlet;the first dump region wall and the second dump region wall defining an expansion cavity, the first dump region wall and the second dump region wall diverging as the expansion cavity extends from the outlet, the first dump region wall diverging in the downstream direction at a second angle relative to the diffuser center axis, wherein the second angle is greater than the first angle;a flow separator extending radially from the first prediffuser wall into the annular cavity proximate and upstream of the outlet, the flow separator having a rectangular profile and extending into the annular prediffuser airflow path through the annular cavity to form a barrier facing the inlet which opposes an airflow along the first prediffuser wall, the flow separator is configured to separate the airflow from the first prediffuser wall before the airflow enters the dump region thereby creating a separated airflow, wherein neither the dump region nor the prediffuser include a vortex chamber or a bleed air port, located adjacent to the flow separator, used to influence the separated airflow adjacent to the barrier; andwherein the diffuser is configured for attachment to an upstream end of a combustor of the gas turbine engine. 2. The diffuser of claim 1, wherein the flow separator includes a height and a width; and wherein a ratio of the width to the height is between 0.6-0.8. 3. The diffuser of claim 1, further comprising a prediffuser-dump region interface between the prediffuser and the dump region; and wherein the flow separator is located proximate the prediffuser-dump region interface. 4. The diffuser of claim 1, wherein the flow separator is integrated into the prediffuser as part of a casting of the prediffuser. 5. The diffuser of claim 1, wherein the flow separator includes a height and a width; andwherein the height of the flow separator is between five and fifteen percent of a distance between the first prediffuser wall and the second prediffuser wall. 6. The diffuser of claim 5, wherein the width of the flow separator is between 0.0625″ and 0.25″. 7. The diffuser of claim 6, wherein the height of the flow separator is between 0.09″ and 0.27″; and wherein the flow separator circumscribes at least one of the first prediffuser wall and the second prediffuser wall. 8. A combustor for use in a gas turbine engine, the combustor including the diffuser of claim 1. 9. A gas turbine engine including the diffuser of claim 1, wherein the gas turbine engine includes a compressor and a turbine; and wherein the diffuser is located downstream of the compressor and upstream of the turbine. 10. A diffuser for use in a gas turbine engine, the diffuser comprising: a dump region including a dump region outer wall and a dump region inner wall defining an expansion cavity;a prediffuser disposed upstream of the dump region, the prediffuser including a prediffuser outer wall and a prediffuser inner wall forming an annular airflow path with an inlet and an outlet, the prediffuser expanding from the inlet to the outlet, the prediffuser outer wall diverging in a downstream direction at a first angle relative to a diffuser center axis;the dump region outer wall extending from the prediffuser outer wall at the outlet and diverging in the downstream direction at a second angle relative to the diffuser center axis, wherein the second angle is greater than the first angle;a flow separator extending radially inward from the prediffuser outer wall into the annular airflow path and toward the prediffuser inner wall proximate and upstream of the dump region, the flow separator having a rectangular profile forming a barrier facing the inlet which opposes an airflow along the prediffuser outer wall and is configured to separate the airflow from the prediffuser outer wall before the airflow enters the dump region thereby creating a separated airflow, the flow separator is configured to direct the separated airflow towards the prediffuser outlet, wherein neither the dump region nor the prediffuser include either of: a vortex chamber or a bleed air port, located adjacent to the flow separator, used to influence the separated airflow adjacent to the barrier; andwherein the diffuser is configured for attachment to an upstream end of a combustor of the gas turbine engine. 11. The diffuser of claim 10, wherein the flow separator includes a height and a width; and wherein the flow separator is located upstream of the dump region by a distance less than 3 times the width of the flow separator. 12. The diffuser of claim 10, wherein the flow separator includes a height and a width; and wherein the flow separator is located upstream of the dump region by a distance between 0.5 times the width and 4.5 times the width of the flow separator. 13. A diffuser for use in a gas turbine engine, the diffuser comprising: an outer housing includinga prediffuser outer wall, anda dump region outer wall extending from the prediffuser outer wall;an inner housing located within the outer housing, the inner housing including a prediffuser inner wall located inward from the prediffuser outer wall, the prediffuser inner wall and the prediffuser outer wall forming a prediffuser that includes an inlet and an outlet and defines an annular prediffuser airflow path from the inlet to the outlet, the prediffuser expanding from the inlet to the outlet, the prediffuser outer wall diverging in a downstream direction at a first angle relative to a diffuser center axis, anda dump region inner wall located inward from the dump region outer wall, the dump region inner wall and the dump region outer wall defining a dump region forming an expansion cavity extending from the prediffuser outlet, the dump region outer wall diverging in the downstream direction at a second angle relative to the diffuser center axis, wherein the second angle is greater than the first angle; anda flow separator extending radially into the annular prediffuser airflow path from the prediffuser outer wall towards the prediffuser inner wall, the flow separator being adjacent to and upstream of the dump region outer wall; andthe flow separator having a rectangular profile forming a barrier which faces the inlet and opposes an airflow along the prediffuser outer wall and is configured to separate the airflow from the prediffuser outer wall thereby creating a separated airflow, the flow separator is configured to direct the separated airflow into the annular prediffuser airflow path prior to the separated airflow entering the dump region, wherein neither the dump region nor the prediffuser include either of: a vortex chamber or a bleed air port, located adjacent to the flow separator, used to influence the separated airflow adjacent to the barrier; andwherein the diffuser forms a portion of a combustor of the gas turbine engine. 14. The diffuser of claim 13, wherein the prediffuser outer wall forms a frustum between the inlet and the outlet, and wherein the prediffuser outer wall expands from the inlet to the outlet. 15. The diffuser of claim 13, wherein the prediffuser outer wall and the prediffuser inner wall include a machined finish, and wherein the dump region outer wall and the dump region inner wall include a cast finish. 16. The diffuser of claim 15, further comprising a prediffuser-dump region interface located at the outlet, wherein the outer housing transitions from the machined finish to the cast finish. 17. The diffuser of claim 13, wherein the outer housing includes a discontinuity in a rate of expansion between the prediffuser outer wall and the dump region outer wall.