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A system for adjusting a clearance between blade tips of a turbine and a shroud assembly encircling the turbine in a turbine engine is disclosed herein. The system includes a first fluid passageway operable to extend from a first source of fluid at a variable pressure to a shroud assembly of a turbi

A system for adjusting a clearance between blade tips of a turbine and a shroud assembly encircling the turbine in a turbine engine is disclosed herein. The system includes a first fluid passageway operable to extend from a first source of fluid at a variable pressure to a shroud assembly of a turbine engine. The first fluid passageway directs a first stream of fluid to the shroud assembly. The system also includes a first valve positioned along the first fluid passageway and moveable between open and closed configurations. The first valve is biased to the open configuration and moved to the closed configuration passively and directly by a first predetermined level of pressure of the first stream of fluid. During periods of relatively low power production of the turbine engine, the first valve is in the open configuration and moves to the closed configuration when power production of the turbine engine increases from relatively low power production.

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1. A system for adjusting a clearance between blade tips of a turbine and a shroud assembly in a turbine engine, the system comprising: a first fluid passageway in fluid communication with a first source of fluid at a first pressure from a first compressor stage of a multi-stage compressor and exten

1. A system for adjusting a clearance between blade tips of a turbine and a shroud assembly in a turbine engine, the system comprising: a first fluid passageway in fluid communication with a first source of fluid at a first pressure from a first compressor stage of a multi-stage compressor and extending between the first compressor stage and a shroud assembly of a turbine engine to direct a first stream of fluid at the first pressure to the shroud assembly;a second fluid passageway in fluid communication with a second source of fluid at a second pressure from a second compressor stage of the multi-stage compressor and extending between the second compressor stage and the shroud assembly to direct a second stream of fluid at the second pressure to the shroud assembly;a first valve positioned along said first fluid passageway and a second valve positioned along said second fluid passageway, each of said first and second valves moveable between open and closed configurations, said first valve controlled passively and directly by the first pressure of the first stream of fluid, said second valve controlled passively and directly by the second pressure of the second stream of fluid;wherein said first and second fluid passageways are in fluid communication with an interior region of said shroud assembly to direct said first and second streams of fluid into said interior region, said first and second fluid streams flow through said interior region of said shroud assembly to thermally expand and contract said shroud assembly to adjust the clearance between the blade tips and the shroud assembly; andwherein said first valve is moved toward said closed configuration when power production of the turbine engine is increased from a period of relatively low power production and/or wherein said second valve is moved toward said open configuration when power production of the turbine engine is increased from a period of relatively low power production. 2. The system of claim 1 wherein said first valve is further defined as a poppet valve. 3. The system of claim 2 wherein said first valve is further defined as being biased to said open configuration by a spring isolated from the first stream of fluid. 4. The system of claim 1 wherein said second valve is further defined as being biased to said closed configuration. 5. The system of claim 1 wherein said second valve is further defined as a one-way check valve urged to said closed configuration by the first stream of fluid. 6. The system of claim 1 wherein said first and second fluid passageways are further defined as partially parallel to one another and partially common to one another. 7. The system of claim 1 wherein said second fluid passageway is further defined as being operable to extend between a bleed opening at an inter-stage portion of the multi-stage compressor and the shroud assembly of the turbine engine. 8. The system of claim 1 wherein said interior region of said shroud assembly comprises an annular chamber that is defined by a ring attached to a blade track; and wherein the clearance is defined between the blade tips and the blade track. 9. The system of claim 1 wherein the second pressure from the second compressor stage is lower than the first pressure from the first compressor stage. 10. The system of claim 1 wherein the first stream of fluid from the first compressor stage is at a first temperature and the second stream of fluid from the second compressor stage is at a second temperature different from the first temperature. 11. The system of claim 1 wherein said first valve biased toward said open configuration and moved toward said closed configuration passively and directly by the first pressure of the first stream of fluid; and wherein said second valve biased toward said closed configuration and moved toward said open configuration passively and directly by the second pressure of the second stream of fluid. 12. A method for adjusting a clearance between blade tips of turbine and a shroud assembly spaced radially outward of the blade tips and comprising the steps of: heating a shroud assembly of a turbine engine with a first stream of fluid directed along a first fluid passageway from an outlet of a compressor section of the turbine engine, the first fluid passageway extending to the shroud assembly;closing the first fluid passageway to stop said heating step with a first valve positioned along the first fluid passageway, wherein said closing step occurs passively and directly in response to a first predetermined level of pressure of the first stream of fluid;wherein the first fluid passageway extends to and is in fluid communication with an interior region of the shroud assembly to direct the first stream of fluid into the interior region, the first fluid stream flows through the interior region of the shroud assembly to thermally expand and contract the shroud assembly to adjust the clearance between the blade tips and the shroud assembly; andwherein said closing step is further defined as occurring when power production of the turbine engine increases from a period of relatively low power production. 13. The method of claim 12 wherein said heating step is further defined as occurring only during periods of relatively low power production of the turbine engine. 14. The method of claim 12 further comprising the steps of: opening a second fluid passageway to direct a second stream of fluid to the shroud assembly from an inter-stage portion of the compressor section to cool the shroud assembly. 15. The method of claim 14 wherein said opening step and said closing step are further defined as being concurrent with one another. 16. The method of claim 14 wherein said opening step is further defined as: opening the second fluid passageway passively and directly in response to a second predetermined level of pressure of the second stream of fluid. 17. The method of claim 14 wherein said opening step is further defined as: opening the second fluid passageway passively and directly in response to a pressure differential between the first and second streams of fluid. 18. The method of claim 14 further comprising the steps of: closing the second fluid passageway with a second valve; andforming the first fluid passageway and the second passageway to be common with one another downstream of the first and second valves to prevent both of the first and second streams of fluid from flowing concurrently to the shroud assembly. 19. The method of claim 12 wherein the interior region of the shroud assembly comprises an annular chamber that is defined by a ring attached to a blade track; and wherein the clearance is defined between the blade tips and the blade track. 20. A method for adjusting a clearance between blade tips of turbine and a shroud assembly spaced radially outward of the blade tips and comprising the steps of: heating a shroud assembly of a turbine engine with a first stream of fluid directed along a first fluid passageway from an outlet of a compressor section of the turbine engine, the first fluid passageway extending to the shroud assembly;closing the first fluid passageway to stop said heating step with a first valve positioned along the first fluid passageway, wherein said closing step occurs passively and directly in response to a first predetermined level of pressure of the first stream of fluid;wherein the first fluid passageway extends to and is in fluid communication with an interior region of the shroud assembly to direct the first stream of fluid into the interior region, the first fluid stream flows through the interior region of the shroud assembly to thermally expand and contract the shroud assembly to adjust the clearance between the blade tips and the shroud assembly;opening a second fluid passageway to direct a second stream of fluid to the shroud assembly from an inter-stage portion of the compressor section to cool the shroud assembly; andwherein said opening step is further defined as occurring only when power production of the turbine engine increases from relatively low power production. 21. The method of claim 20 wherein said opening step and said closing step are further defined as being concurrent with one another. 22. The method of claim 20 wherein said opening step is further defined as: opening the second fluid passageway passively and directly in response to a second predetermined level of pressure of the second stream of fluid. 23. The method of claim 20 wherein said opening step is further defined as: opening the second fluid passageway passively and directly in response to a pressure differential between the first and second streams of fluid. 24. The method of claim 20 further comprising the steps of: closing the second fluid passageway with a second valve; andforming the first fluid passageway and the second passageway to be common with one another downstream of the first and second valves to prevent both of the first and second streams of fluid from flowing concurrently to the shroud assembly. 25. A turbine engine comprising: a multi-stage compressor section;a turbine section having a plurality of turbine blades spaced from said multi-stage compressor section along a centerline axis;a shroud assembly supporting a plurality of blade tracks in radially spaced relation to said turbine blades and defining an annular chamber encircling an axis;a first fluid passageway in fluid communication with an outlet of said multi-stage compressor section and extending to said annular chamber of said shroud assembly to direct a first stream of fluid to said shroud assembly;a first valve positioned along said first fluid passageway and moveable between open and closed configurations, said first valve being biased to said open configuration and moved to said closed configuration passively and directly by a first predetermined level of pressure of the first stream of fluid;a second fluid passageway in fluid communication with an inter-stage portion of said multi-stage compressor section and extending to said annular chamber to direct a second stream of fluid to said annular chamber;a second valve positioned along said second fluid passageway and moveable between open and closed configurations, said second valve moved to said open configuration passively and directly by a second predetermined level of pressure of the second stream of fluid;wherein said first fluid passageway extends to and is in fluid communication with said annular chamber of said shroud assembly to direct said first stream of fluid into said annular chamber, said first fluid stream flows through said annular chamber of said shroud assembly to thermally expand and contract said shroud assembly to adjust the clearance between the blade tips and the blade tracks; andwherein said first and second valves are positioned in circumferentially-spaced relation to one another about said centerline axis. 26. The turbine engine of claim 25 wherein said annular chamber of said shroud assembly is defined by a ring attached to said blade tracks; and wherein the clearance is defined between the blade tips and the blade tracks. 27. A turbine engine comprising: a multi-stage compressor section;a turbine section having a plurality of turbine blades spaced from said multi-stage compressor section along a centerline axis;a shroud assembly supporting a plurality of blade tracks in radially spaced relation to said turbine blades and defining an annular chamber encircling an axis;a first fluid passageway in fluid communication with an outlet of said multi-stage compressor section and extending to said annular chamber of said shroud assembly to direct a first stream of fluid to said shroud assembly;a first valve positioned along said first fluid passageway and moveable between open and closed configurations, said first valve being biased to said open configuration and moved to said closed configuration passively and directly by a first predetermined level of pressure of the first stream of fluid;a second fluid passageway in fluid communication with an inter-stage portion of said multi-stage compressor section and extending to said annular chamber to direct a second stream of fluid to said annular chamber;a second valve positioned along said second fluid passageway and moveable between open and closed configurations, said second valve moved to said open configuration passively and directly by a second predetermined level of pressure of the second stream of fluid;a supplemental cooling system communicating with said second fluid passageway to cool the second fluid stream by directing additional fluid to the second fluid stream; andwherein said first fluid passageway extends to and is in fluid communication with said annular chamber of said shroud assembly to direct said first stream of fluid into said annular chamber, said first fluid stream flows through said annular chamber of said shroud assembly to thermally expand and contract said shroud assembly to adjust the clearance between the blade tips and the blade tracks. 28. The turbine engine of claim 27 wherein said first and second valves are positioned in circumferentially-spaced relation to one another about said centerline axis. 29. The turbine engine of claim 27 wherein said supplemental cooling system includes: a pump;a third valve positioned between said pump and said second fluid passageway and moveable between open and closed configurations to selectively direct the additional fluid to the second fluid stream;a sensor positioned along said second fluid passageway and operable to communicate a signal corresponding to a temperature in said second fluid passageway; anda controller operable to receive the signal from said sensor and control said third valve to move to one of the open and closed configurations.