초록 ▼

An apparatus and a method for cooling and/or sealing a gas turbine by selectively boosting the pressure of air extracted at a lower extraction stage is provided. The pressure of the extracted air is boosted by an external compressor before it becomes available for cooling and/or sealing the turbine

An apparatus and a method for cooling and/or sealing a gas turbine by selectively boosting the pressure of air extracted at a lower extraction stage is provided. The pressure of the extracted air is boosted by an external compressor before it becomes available for cooling and/or sealing the turbine components. A bypass line includes a higher extraction stage providing air for cooling the turbine.

대표청구항 ▼

1. A method for supplying cooling and/or sealing fluid flow in turbomachinery, comprising: a) establishing a first fluid flow in the turbomachinery and flowing the first fluid flow to a first site in the exterior of the turbomachinery;b) establishing a second fluid flow at said first site, said seco

1. A method for supplying cooling and/or sealing fluid flow in turbomachinery, comprising: a) establishing a first fluid flow in the turbomachinery and flowing the first fluid flow to a first site in the exterior of the turbomachinery;b) establishing a second fluid flow at said first site, said second fluid flow having pressure higher than the pressure of said first fluid flow; andc) delivering said second fluid flow to a second site in the interior of the turbomachinery,wherein the step of establishing a first fluid flow includes extracting the first fluid flow from a stage of a compressor forming part of the turbomachinery, and the step of establishing a second fluid flow includes passing the first fluid flow through an external booster compressor, the method further includingestablishing a third fluid flow in the turbomachinery and delivering the third fluid flow into said second site of the turbomachinery, whereinthe step of establishing a third fluid flow in the turbomachinery includes extracting the third fluid flow from another stage of said compressor forming part of the turbomachinery at a pressure higher than the pressure of said first fluid flow. 2. The method of claim 1, wherein the step of delivering the second fluid flow to a second site includes providing said second fluid flow to a gas turbine component forming part of the turbomachinery. 3. The method of claim 1, further comprising passing said first fluid flow through a first isolation valve before it enters said external booster compressor, and passing the fluid flow exiting the external booster compressor through a second isolation valve before it is delivered to said second site. 4. The method of claim 3, wherein said passing of first fluid through said first isolation valve and raising its pressure to required level before delivering it as second fluid through said second isolation valve results in increase in the efficiency of the turbomachinery. 5. The method of claim 1, wherein said second fluid flow provides cooling and sealing air at at least one of the second site and other locations of the turbomachinery. 6. The method of claim 1, further comprising passing said third fluid flow through a modulation valve. 7. The method of claim 1, wherein the temperature of the second fluid flow is lower than that of the third flow, resulting in reduced cooling mass flow requirements, causing increased mass flow to a combustor forming part of the turbomachinery and increase of the output power of the turbomachinery. 8. An apparatus for supplying cooling and/or sealing fluid flow in turbomachinery, comprising: a) a first extraction port for establishing a first fluid flow in the turbomachinery and flowing the first fluid flow to a first site in the exterior of the turbomachinery;b) a component external to the turbomachinery at said first site for establishing a second flow at said first site, said second fluid flow having pressure higher than the pressure of said first fluid flow; whereinsaid second flow is delivered to a second site in the interior of the turbomachinery,wherein the first fluid flow is extracted from a first extraction port of a compressor forming part of the turbomachinery, and said first fluid flow passes through an external booster compressor to establish said second fluid flow, the apparatus further includinga bypass line establishing a third fluid flow in the turbomachinery and delivering the third fluid flow into said second site of the turbomachinery, for increasing the reliability of the turbomachinery system and the capability of retrofitting to the existing system, whereinsaid third fluid flow is extracted from a second extraction port of said compressor forming part of the turbomachinery, said third fluid flow having pressure higher than the pressure of said fist fluid flow extracted from said first extraction port. 9. The apparatus of claim 8, wherein the second fluid flow is delivered to a gas turbine component forming part of the turbomachinery. 10. The apparatus of claim 8, wherein the booster compressor may be powered using one of thermal, electrical, hydraulic, chemical energy or a combination thereof. 11. The apparatus of claim 8, further comprising a first isolation valve positioned between said first extraction port and said external booster compressor, and a second isolation valve positioned between said external booster and said second site. 12. The apparatus of claim 8, wherein said second flow provides cooling and sealing air at at least one of said second site and other locations of the turbomachinery. 13. The apparatus of claim 8, further comprising a modulation valve positioned between said second extraction port and said second site. 14. The apparatus of claim 8, wherein the temperature of the second fluid flow is lower than that of the third flow, resulting in reduced cooling mass flow requirements, causing increased mass flow to a combustor forming part of the turbomachinery and increase of the output power of the turbomachinery.