Profile matched diffuser

Claim 2

In a gas turbine engine diffuser for diffusing compressed airflow received from a compressor, said compressor having a diffuser first channel and a diffuser second channel disposed in parallel flow communication relative to a flow splitter having a leading edge, a method of diffusing said airflow comprising: diffusing a first portion of said airflow in said first channel at a first rate of diffusion; diffusing a second portion of said airflow in said second channel at a second rate of diffusion; and said first and second diffusion rates being unequal.

Claim 3

A method of diffusing airflow according to claim 1 further including providing said diffuser with said airflow having a nonsymmetrical velocity profile across said diffuser, said velocity profile including a peak velocity in said airflow second portion, and channeling said airflow second portion into said second channel, and said first diffusion rate being greater than said second diffusion rate.

Claim 4

A method of diffusing airflow according to claim 2 wherein said first and second channels have first and second area ratios, respectively, and said first area ratio is greater than said second area ratio.

Claim 5

A method of diffusing airflow according to claim 3 further including diffusing said first and second airflow portions at said first and second diffusion rates for obtaining substantially symmetrical streamlines of said airflow over said splitter leading edge.

Claim 6

A method of diffusing airflow according to claim 1 further including diffusing said first and second airflow portions at said first and second diffusion rates for obtaining substantially symmetrical streamlines of said airflow over said splitter leading edge.

Claim 7

A diffuser for a gas turbine engine having a compressor providing compressed airflow comprising: a first wall; a second wall spaced from said first wall; a flow splitter having a leading edge and an aft end and disposed between said first and second walls to define with said first wall a first channel therebetween for diffusing a first portion of said airflow channeled therethrough, and to define with said second wall a second channel therebetween for diffusing a second portion of said airflow channeled therethrough; said first channel having a first inlet defined between said first wall and said splitter leading edge for receiving said airflow first portion, and a first outlet defined between said first wall and said splitter aft end, said first inlet having a first inlet flow area and said first outlet having a first outlet flow area, said first outlet flow area over said first inlet flow area defining a first area ratio for diffusing said airflow first portion in said channel; said second channel having a second inlet defined between said second wall and said splitter leading edge for receiving said second airflow portion, and a second outlet defined between said second wall and said splitter aft end, said second inlet having a second inlet flow area and said second outlet having a second outlet flow area, said second outlet flow area over said second inlet flow area defining a second area ratio for diffusing said airflow second portion in said second channel; and said first and second area ratios being unequal.

Claim 8

A diffuser for a gas turbine engine having a compressor providing compressed airflow comprising: a first wall; a second wall spaced from said first wall; a flow splitter having a leading edge and an aft end and disposed between said first and second walls to define with said first wall a first channel therebetween for diffusing a first portion of said airflow channeled therethrough, and to define with said second wall a second channel therebetween for diffusing a second portion of said airflow channeled therethrough; said first channel having a first inlet defined between said first wall and said splitter leading edge for receiving said airflow first portion, and a first outlet defined between said first wall and said splitter aft end, said first inlet having a first inlet flow area and said first outlet having a first outlet flow area, said first outlet flow area over said first inlet flow area defining a first area ratio for diffusing said airflow first portion in said channel; said second channel having a second inlet defined between said second wall and said splitter leading edge for receiving said second airflow portion, and a second outlet defined between said second wall and said splitter aft end, said second inlet having a second inlet flow area and said second outlet having a second outlet flow area, said second outlet flow area over said second inlet flow area defining a second area ratio for diffusing said airflow second portion in said second channel; and said first and second area ratios being unequal.

Claim 9

A diffuser according to claim 6 wherein said compressor is effective for providing said airflow with a nonsymmetrical velocity profile including a peak velocity in said airflow second portion, said second channel is alignable with said compressor for receiving said airflow second portion, and said first area ratio is greater than said second area ratio.

Claim 10

A diffuser according to claim 7 wherein said compressor is an axial flow compressor and said first channel is disposed radially outwardly of said second channel.

Claim 11

A diffuser according to claim 7 wherein said first channel is sized for receiving said airflow first portion at a first flow rate, said second channel is sized for receiving said airflow second portion at a second flow rate, and said first and second flow rates and said first and second area ratios are preselected so that both said first and second channels effect substantially equal first and second flow separation margins, respectively.

Claim 12

A diffuser according to claim 9 wherein said first and second flow rates are unequal.

Claim 13

A diffuser according to claim 9 wherein said first and second flow rates are equal.