Flange with axially extending holes for gas turbine engine clearance control
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-025/14
F01D-025/24
출원번호
US-0771333
(2007-06-29)
등록번호
US-8197186
(2012-06-12)
발명자
/ 주소
Dong, Zhifeng
Rahaim, John Joseph
출원인 / 주소
General Electric Company
대리인 / 주소
William Scott Andes
인용정보
피인용 횟수 :
2인용 특허 :
15
초록▼
A gas turbine engine annular turbine casing having an annular shell, axially spaced apart forward and aft flanges extending radially outwardly from the shell, forward and aft case hooks depending radially inwardly from the annular shell, and an axially curved surface at an outer diameter of the aft
A gas turbine engine annular turbine casing having an annular shell, axially spaced apart forward and aft flanges extending radially outwardly from the shell, forward and aft case hooks depending radially inwardly from the annular shell, and an axially curved surface at an outer diameter of the aft flange. The axially curved surface may be a semi-spherical surface. The forward and aft case hooks may be located axially near or at the forward and aft flanges respectively. A circular row of holes may be axially disposed through the aft flange circumscribing the central axis and radially located between the outer diameter of the aft flange and the annular shell. An annular manifold spaced radially outwardly of the shell forming an annular space between the manifold and the shell and having impingement holes disposed through the manifold may be used for impinging cooling air on the axially curved surface.
대표청구항▼
1. A gas turbine engine turbine assembly comprising: an annular turbine casing having an annular shell circumscribed about a central axis,axially spaced apart forward and aft flanges extending radially outwardly from the annular shell,forward and aft case hooks depending radially inwardly from the a
1. A gas turbine engine turbine assembly comprising: an annular turbine casing having an annular shell circumscribed about a central axis,axially spaced apart forward and aft flanges extending radially outwardly from the annular shell,forward and aft case hooks depending radially inwardly from the annular shell of the casing,a shroud assembly depending radially inwardly from the turbine casing and being connected to the forward and aft case hooks,a circular row of axially extending cooling holes disposed through the aft flange circumscribing the central axis and radially located between an outer diameter of the aft flange and the annular shell,a radially outwardly facing annular impingement surface of the aft flange at the outer diameter of the aft flange,an annular manifold circumscribing the central axis and spaced radially outwardly of the annular shell,an annular space disposed between the manifold and the annular shell,impingement holes disposed through the manifold and located for spraying cooling air radially inwardly and directly on the annular impingement surface of the aft flange,radially outwardly facing cylindrical surfaces at outer diameters of the forward and rear flanges and the radially outwardly facing annular impingement surface of the aft flange being axially curved, andthe axially curved annular impingement surface being semi-spherical, having a radius of curvature, and the radius of curvature having an origin on the central axis. 2. A gas turbine engine turbine assembly as claimed in claim 1 further comprising the forward and aft case hooks being located axially near or at the forward and aft flanges respectively. 3. A gas turbine engine turbine assembly as claimed in claim 2 further comprising: a rear flange extending radially outwardly from a rear end of the annular shell,a rear case hook depending radially inwardly from the annular shell, andthe rear case hook being axially located at or near the rear end of the annular shell. 4. A gas turbine engine turbine assembly comprising: an annular turbine casing having an annular shell circumscribed about a central axis,axially spaced apart forward and aft flanges extending radially outwardly from the annular shell,a rear flange extending radially outwardly from a rear end of the annular shell,forward and aft case hooks depending radially inwardly from the annular shell of the casing,a shroud assembly depending radially inwardly from the turbine casing and being connected to the forward and aft case hooks,a circular row of axially extending cooling holes disposed through the aft flange circumscribing the central axis and radially located between the outer diameter of the aft flange and the annular shell,radially outwardly facing cylindrical surfaces at outer diameters of the forward and rear flanges, anda radially outwardly facing axially curved annular impingement surface of the aft flange at an outer diameter of the aft flange,an annular manifold circumscribing the central axis and spaced radially outwardly of the annular shell,an annular space disposed between the manifold and the annular shell, andimpingement holes disposed through the manifold and located for spraying cooling air radially inwardly and directly on the axially curved surface and the cylindrical surfaces, andthe axially curved surface being a semi-spherical surface having a radius of curvature and the radius of curvature having an origin on the central axis. 5. A turbine assembly as claimed in claim 4 further comprising: the shroud assembly including a plurality of arcuate shroud segments coupled to segmented shroud hangers,the shroud hangers being supported by segmented shroud supports depending radially inwardly from the turbine casing, andforward and aft ends of the shroud support being supported by the forward and aft case hooks respectively. 6. A turbine assembly as claimed in claim 5 further comprising the forward and aft case hooks being located axially near or at the forward and aft flanges respectively. 7. A turbine assembly as claimed in claim 4 further comprising the circular row of axially extending cooling holes operable to flow the cooling air therethrough after the cooling air is sprayed on the annular impingement surface.
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이 특허에 인용된 특허 (15)
Burdgick Steven S. (Clifton Park NY) Hess John R. (Clifton Park NY) Mercer Gary D. (Ballston Lake NY) Crum Gregory A. (Greenville SC) Cencula James E. (Ballston Lake NY) Eastman John A. (Clifton Park, Casing distortion control for rotating machinery.
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.
Friedel Jerome,FRX ; Lestoille Patrick Didier Michel,FRX ; Schultz Christophe,FRX ; Soupizon Jean-Luc,FRX ; Vache Jean Bernard,FRX, Device for cooling or heating a circular housing.
Proctor Robert ; Epstein Michael J. ; Fraser Gordon G. ; Farley Scott E. ; Koch Richard F. ; Siebert Robert W., External cooling system for turbine frame.
Plemmons Larry W. (Fairfield OH) Proctor Robert (West Chester OH) Albers Robert J. (Park Hills KY) Gardner Donald L. (West Chester OH), Gas turbine engine case counterflow thermal control.
Ritchie Julie A. (Cincinnati OH) Schleue Joseph H. (Cincinnati OH) Glover Jeffrey (Cincinnati OH) Tegarden Frederick W. (Glendale OH), Integral clearance control impingement manifold and environmental shield.
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