A system and method for actively managing blade tip clearances in a turbine engine, particularly under steady state operating conditions such as at base load, involves routing a portion of air from a rotor cooling air circuit to a vane carrier or other stationary support structure surrounding the tu
A system and method for actively managing blade tip clearances in a turbine engine, particularly under steady state operating conditions such as at base load, involves routing a portion of air from a rotor cooling air circuit to a vane carrier or other stationary support structure surrounding the turbine blades. Because the temperature of the air is less than the temperature of the stationary support structure, the stationary support structure will thermally contract when the air is passed in heat exchanging relation therewith. In one embodiment, the air can be passed through one or more passages extending through at least a portion of the stationary support structure. The contraction of the stationary support structure reduces the blade tip clearance because the blades do not contract. Thus, fluid leakage through the clearances is minimized, which in turn can increase engine performance.
대표청구항▼
What is claimed is: 1. A blade tip clearance control system comprising a turbine engine having a compressor section, a combustor section having a chamber receiving compressed air from the compressor section, and a turbine section, wherein the turbine section includes a plurality of discs mounted to
What is claimed is: 1. A blade tip clearance control system comprising a turbine engine having a compressor section, a combustor section having a chamber receiving compressed air from the compressor section, and a turbine section, wherein the turbine section includes a plurality of discs mounted to a rotor, wherein a plurality of blades are attached to the discs, each blade extending radially outward from the respective disc to a tip; a stationary support structure substantially surrounding at least a portion of the blades, wherein a clearance is defined between the tips of the blades and the stationary support structure, the stationary support structure being at a first temperature; a rotor cooling air circuit including a fluid conduit and a cooler disposed along the fluid conduit, the fluid conduit being connected in fluid communication with the chamber of the combustor section such that a portion of the compressed air in the chamber is received within the fluid conduit, wherein the portion of compressed air passes in heat exchanging relation with the cooler such that the temperature of the portion of air is reduced to a second temperature, wherein the second temperature is less than the first temperature, wherein the cooler is external to the chamber of the combustor section, and wherein the fluid conduit downstream of the cooler is initially external to the chamber of the combustor section and then enters the chamber of the combustor section; and a supply conduit connected in fluid communication with the fluid conduit at a point within the chamber and extending therefrom, the supply conduit extending entirely within the chamber, wherein the supply conduit routes at least a portion of the air at the second temperature to the stationary support structure so that the air passes in heat exchanging relation with the stationary support structure, whereby the stationary support structure contracts to reduce the clearance. 2. The system of claim 1 wherein the stationary support structure is at least one of a vane carrier, a ring seal and an outer casing. 3. The system of claim 1 wherein at least one passage extends through at least a portion of the stationary support structure, the passage having an inlet and an outlet, wherein the supply conduit is connected in fluid communication with the inlet of the passage such that the passage receives the air at the second temperature. 4. The system of claim 1 further including a return conduit positioned to receive the air that has passed in heat exchanging relation with the stationary support structure, wherein the return conduit is connected in fluid communication with the fluid conduit downstream of the area where the supply conduit connects to the fluid conduit, whereby air that has passed in heat exchanging relation with the stationary support structure is routed back to the fluid conduit. 5. The system of claim 4 further including a temperature measurement device operatively associated with the fluid conduit downstream of the area where the return conduit connects to the fluid conduit. 6. The system of claim 1 further including a valve operatively positioned along one of the fluid conduit and the supply conduit to selectively permit and prohibit the supply of air at the second temperature to the stationary support structure. 7. The turbine system of claim 6 wherein, at base load engine operation, the valve permits the supply air at the second temperature to the stationary support structure. 8. A blade tip clearance control system comprising a turbine engine having a compressor section, a combustor section having a chamber receiving compressed air from the compressor section, and a turbine section, wherein the turbine section including a plurality of discs mounted to a rotor, wherein a plurality of blades are attached to the discs, each blade extending radially outward from a respective one of the discs to a tip; a stationary support structure substantially surrounding at least a portion of the blades, wherein a clearance is defined between the tips of the blades and the stationary support structure, the stationary support structure having at least one passage extending therethrough, the passage having an inlet end and an outlet end, the stationary support structure being at a first temperature; a rotor cooling air circuit including a fluid conduit and a cooler disposed along the fluid conduit, the fluid conduit connected in fluid communication with the chamber of the combustor section such that a portion of the compressed air in the chamber is received within the fluid conduit, wherein the portion of compressed air passes in heat exchanging relation with the cooler such that the temperature of the portion of air is reduced to a second temperature, wherein the second temperature is less than the first temperature; a supply conduit connecting between and in fluid communication with the fluid conduit and the inlet end of the passage, wherein the supply conduit routes at least a portion of the air at the second temperature to the passage, wherein the air passes through the passage in heat exchanging relation with the stationary support structure, whereby the stationary support structure contracts to reduce the clearance; a return conduit connecting between and in fluid communication with the outlet end of the passage and the fluid conduit, wherein the return conduit connects to the fluid conduit downstream of the area where the supply conduit connects to the fluid conduit, whereby air exiting the passage is routed back to the rotor cooling air circuit; and a valve operatively positioned along one of the fluid conduit and the supply conduit to selectively permit and prohibit the supply of air at the second temperature to the stationary support structure. 9. The system of claim 8 further including a temperature measurement device operatively associated with the fluid conduit downstream of the area where the return conduit connects to the fluid conduit, wherein the temperature measurement device is operatively connected to the cooler, whereby the temperature of the coolant exiting the cooler can be altered as necessary. 10. The system of claim 8 wherein the stationary support structure is one of a vane carrier, a ring seal and an outer casing.
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이 특허에 인용된 특허 (46)
Davison Samuel H. (Loveland OH) Kast Kevin H. (Cincinnati OH) Clark Aidan W. (Blue Ash OH), Active clearance control.
Johnston Richard P. (Morrow OH) Knapp Malcolm H. (South Lynnfield MA) Coulson Charles E. (Danvers MA), Active clearance control system for a turbomachine.
Bessette Alan D. (Palm Beach Gardens FL) Davies Daniel O. (West Palm Beach FL) Shade John L. (Jupiter FL), Combined turbine stator cooling and turbine tip clearance control.
Walker Roger C. (Middletown OH) Fallon Richard J. (West Chester OH) Rieck ; Jr. Harold P. (West Chester OH) Bibler John D. (Cincinnati OH), Compressor casing assembly.
Redinger ; Jr. Ira H. (Vernon CT) Sadowsky David (South Windsor CT) Stripinis Philip S. (South Windsor CT), External gas turbine engine cooling for clearance control.
Hultgren Kent Goran ; Zagar Thomas Walter ; North William E. ; Robbins Stephen Humphrey,GBX ; Upton Graham Mark,GBX, Gas turbine blade platform cooling concept.
Scott Richard Zearbaugh ; Steven Louis Brickner ; James Warren Hackler ; Lonnie Ray Chadwell, Methods and apparatus for maintaining rotor assembly tip clearances.
Sexton Brendan F. ; Knuijt Hans M. ; Eldrid Sacheverel Q. ; Myers Albert ; Coneybeer Kyle E. ; Johnson David Martin ; Kellock Iain R., Removable inner turbine shell with bucket tip clearance control.
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Proctor Robert (West Chester OH) Plemmons Larry W. (Fairfield OH) Brainch Gulcharan S. (West Chester OH) Hess John R. (West Chester OH) Albers Robert J. (Park Hills KY), Shroud cooling assembly for gas turbine engine.
Walker Alan (Wyoming OH) Wakeman Thomas G. (Lawrenceburg IN) Lenahan Dean T. (Cincinnati OH) Plemmons Larry W. (Fairfield OH) Elovic Andrew P. (Rishon Lezion ILX), Turbine shroud clearance control assembly.
Araki, Masato; Iwasaki, Yoshifumi, Method of preventing deformation in gas turbine casing, purging device for executing this method, and gas turbine provided with this device.
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