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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 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.

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1. A compressor, comprising: a rotating compressor blade having a blade tip;an outer compressor case and an inner compressor case, the inner compressor case having a blade track disposed opposite the blade tip; anda tip clearance control system including a fluid impingement structure having a plural

1. A compressor, comprising: a rotating compressor blade having a blade tip;an outer compressor case and an inner compressor case, the inner compressor case having a blade track disposed opposite the blade tip; anda tip clearance control system including a fluid impingement structure having a plurality of impingement openings configured to impinge a fluid onto the inner compressor case;a valve in communication with the fluid impingement structure to control flow of the fluid received from a diffuser downstream from the compressor such that the fluid from the diffuser travels radially through an opening of the diffuser to a cooler, whereinthe cooler is in fluid communication with the fluid impingement structure to cool the fluid, wherein the tip clearance control system is configured to control a clearance between the blade tip and the blade track by impinging the cooled fluid that has been cooled by the cooler onto the inner compressor case and wherein the valve is configured to modulate the cooled fluid between different flow amounts of the cooled fluid, and wherein the diffuser is in fluid communication with the fluid impingement structure through the cooler and the valve and a distribution channel; anda first support structure and a second support structure both configured for radial flexibility, wherein the first support structure and the second support structure absorb a thermal growth differential between the inner compressor case and the outer compressor case resulting from impingement of the cooled fluid onto the inner compressor case, wherein the first support structure includes a first connector attached to the outer compressor case and a second connector attached to the inner compressor case, wherein the first support structure is angled between the first connector and the second connector, wherein the second support structure includes a third connector attached to the outer compressor case, and wherein the second support structure has a bended knee shape and connects the outer compressor case to the inner compressor case. 2. The compressor of claim 1, wherein the fluid is air compressed by the compressor. 3. The compressor of claim 1, wherein the inner compressor case is mechanically supported by the outer compressor case. 4. The compressor of claim 3, wherein the first support structure connects the inner compressor case to the outer compressor case and is radially flexible such that based on the cooled fluid via the cooler, the first support structure contracts and the inner compressor case is moved radially toward the outer compressor case resulting in the clearance between the blade tip and the blade track. 5. The compressor of claim 4, wherein the second support structure extends between the inner compressor case and the outer compressor case, wherein the cooled fluid is supplied to the plurality of impingement openings via a supply opening in the outer compressor case; and wherein the first support structure and the second support structure form a distribution channel configured to distribute the cooled fluid from the supply opening for impingement upon the inner compressor case. 6. The compressor of claim 1, wherein the fluid impingement structure is an impingement plate having the plurality of impingement openings therein; and wherein the impingement plate is disposed adjacent to at least part of the inner compressor case. 7. The compressor of claim 1, wherein at least one of the impingement openings is angled radially inward toward the center of rotation of the rotating compressor blade. 8. The compressor of claim 1, further comprising a compressor flowpath, wherein the compressor is configured to discharge the cooled fluid into the compressor flowpath after impingement of the cooled fluid onto the inner compressor case. 9. A gas turbine engine, comprising: a compressor including a rotating compressor blade having a blade tip, an outer compressor case and an inner compressor case, the inner compressor case disposed opposite the blade tip;a fluid impingement structure having a plurality of impingement openings configured to impinge a fluid onto the inner compressor case;a cooler in fluid communication with the fluid impingement structure to cool the fluid;a diffuser downstream from the compressor to receive a working fluid discharge from the compressor, wherein the diffuser is in fluid communication with the fluid impingement structure and is configured to provide the fluid to the fluid impingement structure such that the fluid from the diffuser travels radially through an opening of the diffuser through the cooler and a distribution channel;a combustor in fluid communication with the compressor through the diffuser;a turbine in fluid communication with the combustor; anda first support structure and a second support structure both configured for radial flexibility, wherein the first support structure and the second support structure absorb a thermal growth differential between the inner compressor case and the outer compressor case resulting from impingement of the cooled fluid that has been cooled by the cooler onto the inner compressor case, wherein the first support structure includes a first connector attached to the outer compressor case and a second connector attached to the inner compressor case, wherein the first support structure is angled between the first connector and the second connector, wherein the second support structure includes a third connector attached to the outer compressor case, and wherein the second support structure has a bended knee shape and connects the outer compressor case to the inner compressor case. 10. The gas turbine engine of claim 9, wherein the cooler is a heat exchanger. 11. The gas turbine engine of claim 9, further comprising a valve configured to control a flow of the cooled fluid, wherein the valve is fluidly disposed upstream of the plurality of impingement openings. 12. The gas turbine engine of claim 11, wherein the valve is configured to modulate the flow of the cooled fluid between a maximum flow amount and a minimum flow amount. 13. The gas turbine engine of claim 9, wherein the first support structure and the second support structure connect the inner compressor case to the outer compressor case, and are radially flexible such that based on the cooled fluid via the cooler, the first support structure and the second support structure contract and the inner compressor case is moved radially toward the outer compressor case resulting in a clearance between the blade tip and the inner compressor case. 14. A gas turbine engine, comprising: a compressor including a rotating compressor blade having a blade tip, an outer compressor case and an inner compressor case, the inner compressor case disposed opposite the blade tip;a diffuser downstream from the compressor receiving a working fluid discharge from the compressor, the diffuser including a pathway to provide a portion of the working fluid discharge as a fluid flow toward the compressor;a combustor structured to receive the working fluid discharge from the compressor through the diffuser;a turbine in fluid communication with the combustor; anda tip clearance control system configured to provide a clearance between the blade tip and the inner compressor case by impinging the fluid flow onto the inner compressor case, the tip clearance control system includinga cooler configured to receive the fluid flow from the diffuser and cool the fluid flow to the compressor;a fluid impingement structure having a plurality of impingement openings configured to impinge the cooled fluid flow onto the inner compressor case;a valve configured to receive the cooled fluid flow from the cooler and provide the cooled fluid flow to the compressor, the valve being configured to modulate the cooled fluid flow between different flow amounts of the cooled fluid flow;wherein the diffuser is in fluid communication with the inner compressor case and is configured to provide the fluid to the inner compressor case such that the fluid from the diffuser travels radially through an opening of the diffuser through the cooler and the valve and a distribution channel; anda first support structure and a second support structure both configured for radial flexibility, wherein the first support structure and the second support structure absorb a thermal growth differential between the inner compressor case and the outer compressor case resulting from impingement of the cooled fluid onto the inner compressor case, wherein the first support structure includes a first connector attached to the outer compressor case and a second connector attached to the inner compressor case, wherein the first support structure is angled between the first connector and the second connector, wherein the second support structure includes a third connector attached to the outer compressor case, and wherein the second support structure has a bended knee shape and connects the outer compressor case to the inner compressor case.