Abstract: A unique compressor includes a rotating compressor blade having a blade tip; a compressor case having a blade track disposed opposite the blade tip; and a tip clearance control system including a fluid impingement structure. This structure has a plurality of openings to impinge a fluid received from a diffuser onto the compressor case. The tip clearance control system is configured to control a clearance between the blade tip and the blade track by impinging the fluid onto the compressor case and modulating the same with a valve in fluid communication with the diffuser. A further form includes a unique gas turbine engine having a compressor with a compressor blade tip, a compressor case disposed opposite the blade tip, and a fluid impingement structure having openings to impinge a fluid onto the case. Also included are other apparatuses, systems, devices, hardware, methods, and combinations for compressor blade tip clearance control.

Abstract: One embodiment of the present invention is a unique compressor. Another embodiment of the present invention is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for blade tip clearance control for compressors and gas turbine engine compressors. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.