Compressor endwall treatment

Details Compressor endwall treatment Compressor endwall treatment

1994-12-05

1996-05-28

Kwon, John T.

Rotary kinetic fluid motors or pumps

With sound or vibratory wave absorbing or preventing means...

4151731, 415914, F01D 510

Patent

active

055205089

ABSTRACT:
The compressor section of an insert gas turbine engine contains a insert installed around the compressor blades that includes cells in a honeycomb configuration. Each cell is inclined at a compound angle to the blade tip to energize the tip air flow as the tip passes over the cell as the blade rotates, improving stall margin with minimum efficiency loss. Each cell is oriented in the direction of the blade chord and faces the advancing blades. As the blade rotates, it sweeps by each cell and high pressure airflow is first captured in the cell from the high pressure side of the blade and released to the low pressure side as the blade passes the cell in the form of a transient energizing jet of high velocity flow in the direction of the airflow across the blade thereby providing effective mixing of the endwall flows and enhancing the tip flow streamwise momentum.

REFERENCES:
patent: 3365172 (1968-01-01), McDonough et al.
patent: 4086022 (1978-04-01), Freeman et al.
patent: 4540335 (1985-09-01), Yamaguchi et al.
patent: 4714406 (1987-12-01), Hough
patent: 4781530 (1988-11-01), Lauterbach et al.
patent: 5160248 (1992-11-01), Clarke

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