A turbomachine, especially a gas turbine, includes a rotor having rotating blades and a stator having a housing and guide blades. The rotating blades form at least one rotating blade ring, which at one radially outward lying end adjoins an inner ring or casing ring of the housing, thereby defining a
A turbomachine, especially a gas turbine, includes a rotor having rotating blades and a stator having a housing and guide blades. The rotating blades form at least one rotating blade ring, which at one radially outward lying end adjoins an inner ring or casing ring of the housing, thereby defining a gap therebetween. The casing ring is connected to a support ring via curved walls, which together with the casing ring and the support ring bound a cavity and form a bellowslike structure. By changing the pressure prevailing in the cavity of the respective bellowslike structure, the gap between the casing ring and the radially outward lying ends of the respective rotating blade ring can be pneumatically adjusted.
대표청구항▼
1. A gas turbine comprising: a stator having a housing and guide blades; the housing defining an axial direction and including annular first, second and third casing rings and annular first and second support rings;the first casing ring being disposed within the first support ring and connected to t
1. A gas turbine comprising: a stator having a housing and guide blades; the housing defining an axial direction and including annular first, second and third casing rings and annular first and second support rings;the first casing ring being disposed within the first support ring and connected to the first support ring via a pair of spaced-apart first curved walls, which first curved walls together with the first casing ring and the first support ring bound a first cavity and form a first bellows-like structure, each of the first curved walls having only a single curve in the axial direction in the region of the first bellows-like structure;the second casing ring being axially spaced-apart from the first casing ring and disposed within the second support ring and connected to the second support ring via a pair of spaced-apart second curved walls, which second curved walls together with the second casing ring and the second support ring bound a second cavity and form a second bellows-like structure, each of the second curved walls having only a single curve in the axial direction in the region of the second bellows-like structure;the third casing ring being axially disposed between the first and second casing rings;a first rotor having a plurality of rotating blades disposed within the housing; the rotating blades forming a first blade ring disposed within the first casing ring;the radially outward lying ends of the blades forming the first blade ring being radially adjacent to the surrounding first casing ring and defining a first radial gap therebetween;a second rotor having a plurality of rotating blades disposed within the housing; the rotating blades forming a second blade ring disposed within the second casing ring;the radially outward lying ends of the blades forming the second blade ring being radially adjacent to the surrounding second casing ring and defining a second radial gap therebetween;a third rotor having a plurality of rotating blades disposed within the housing; the rotating blades forming a third blade ring disposed within the third casing ring;the radially outward lying ends of the blades forming the third blade ring being radially adjacent to the surrounding third casing ring and defining a third radial gap therebetween;a first pressurized air source and drain operatively connected to the first bellows-like structure and adapted to change the prevailing pressure within the first cavity, whereby a change in the prevailing pressure within the first cavity will selectively deform the first bellows-like structure to change the first radial gap between the first blade ring and the first casing ring;a second pressurized air source and drain operatively connected to the second bellows-like structure and adapted to change the prevailing pressure within the second cavity, whereby a change in the prevailing pressure within the second cavity will selectively deform the second bellows-like structure to change the second radial gap between the second blade ring and the second casing ring;a sensor unit operatively connected to the third casing ring, the sensor unit adapted to measure the third radial gap between the third blade ring and the third casing ring and transmit a first value corresponding to a radial dimension of the third radial gap;a feedback control mechanism operatively connected to the first and second pressurized air sources and drains and to the sensor unit, the feedback control mechanism adapted to receive the first value corresponding to the radial dimension of the third radial gap, compare the first value to a second value corresponding to a desired value, and depending on the difference between the first value and the second value, adjust the pressure prevailing in the first and second cavities of the first and second bellows-like structures so that the first value subsequently moves toward the desired value;wherein the feedback control mechanism includes a common valve operatively connected to the first and second pressurized air sources and drains for adding and releasing air from the first and second cavities to maintain the same prevailing pressure within the cavities; andwherein the first blade ring has a first radial dimension and the second blade ring has a second radial dimension that is different from the first radial dimension;the first curved walls of the first bellows-like structure have a first profile and the second curved walls of the second bellows-like structure have a second profile that is different from the first profile; andthe first and second profiles being selected to produce different deformations of the first and second bellows-like structures in response to changes in the same prevailing pressure within the first and second cavities, whereby the different radial dimensions of the first and second rotating blade rings are accommodated. 2. A gas turbine in accordance with claim 1, wherein the first and second profiles are characterized by different curvatures of the first curved walls compared to the second curved walls, taken in the axial direction. 3. A gas turbine in accordance with claim 1, wherein the first and second profiles are characterized by different wall thicknesses of the first curved walls compared to the second curved walls, taken in the axial direction. 4. A gas turbine comprising: a stator having a housing and guide blades; the housing defining an axial direction and including annular first, second and third casing rings and annular first and second support rings;the first casing ring being disposed within the first support ring and connected to the first support ring via a pair of spaced-apart first curved walls, which first curved walls together with the first casing ring and the first support ring bound a first cavity and form a first bellows-like structure;the second casing ring being axially spaced-apart from the first casing ring and disposed within the second support ring and connected to the second support ring via a pair of spaced-apart second curved walls, which second curved walls together with the second casing ring and the second support ring bound a second cavity and form a second bellows-like structure;the third casing ring being axially disposed between the first and second casing rings;a first rotor having a plurality of rotating blades disposed within the housing; the rotating blades forming a first blade ring disposed within the first casing ring;the radially outward lying ends of the blades forming the first blade ring being radially adjacent to the surrounding first casing ring and defining a first radial gap therebetween;a second rotor having a plurality of rotating blades disposed within the housing; the rotating blades forming a second blade ring disposed within the second casing ring;the radially outward lying ends of the blades forming the second blade ring being radially adjacent to the surrounding second casing ring and defining a second radial gap therebetween;a third rotor having a plurality of rotating blades disposed within the housing; the rotating blades forming a third blade ring disposed within the third casing ring;the radially outward lying ends of the blades forming the third blade ring being radially adjacent to the surrounding third casing ring and defining a third radial gap therebetween;a first pressurized air source and drain operatively connected to the first bellows-like structure and adapted to change the prevailing pressure within the first cavity, whereby a change in the prevailing pressure within the first cavity will selectively deform the first bellows-like structure to change the first radial gap between the first blade ring and the first casing ring;a second pressurized air source and drain operatively connected to the second bellows-like structure and adapted to change the prevailing pressure within the second cavity, whereby a change in the prevailing pressure within the second cavity will selectively deform the second bellows-like structure to change the second radial gap between the second blade ring and the second casing ring;a sensor unit operatively connected to a selected one of the first, second and third casing rings, the sensor unit adapted to measure the associated radial gap between the selected one of the casing rings and the associated blade ring and transmit a first value corresponding to a radial dimension of the associated radial gap;a feedback control mechanism operatively connected to the first and second pressurized air sources and drains and to the sensor unit, the feedback control mechanism including a common valve operatively connected to the first and second pressurized air sources and drains for adding and releasing air from the first and second cavities to maintain the same prevailing pressure within the cavities, the feedback control mechanism being adapted to receive the first value corresponding to the radial dimension of the associated radial gap, compare the first value to a second value corresponding to a desired value, and depending on the difference between the first value and the second value, adjust the pressure prevailing in the first and second cavities of the first and second bellows-like structures so that the first value subsequently moves toward the desired value;wherein the first blade ring has a first radial dimension and the second blade ring has a second radial dimension that is different from the first radial dimension;the first curved walls of the first bellows-like structure have a first profile and the second curved walls of the second bellows-like structure have a second profile that is different from the first profile; andthe first and second profiles being selected to produce different deformations of the first and second bellows-like structures in response to changes in the same prevailing pressure within the first and second cavities, whereby the different radial dimensions of the first and second rotating blade rings are accommodated.
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이 특허에 인용된 특허 (9)
Johnston Richard P. (Morrow OH) Knapp Malcolm H. (South Lynnfield MA) Coulson Charles E. (Danvers MA), Active clearance control system for a turbomachine.
Delvaux John M. (Royal Palm Beach FL) Roberts ; Jr. William E. (Newport Beach CA), Adjustable clearance control for rotor blade tips in a gas turbine engine.
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.
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