Turbine nozzle outer band and airfoil cooling apparatus
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-009/04
F01D-025/00
F01D-005/18
출원번호
US-0662284
(2012-10-26)
등록번호
US-9845691
(2017-12-19)
발명자
/ 주소
Allen, Marshall Scott
Correia, Victor Hugo Silva
Proctor, Robert
Buhler, Jared Peter
출원인 / 주소
General Electric Company
대리인 / 주소
General Electric Company
인용정보
피인용 횟수 :
0인용 특허 :
17
초록▼
A turbine nozzle segment includes: an arcuate outer band segment; an airfoil-shaped turbine vane extending radially inward from the outer band segment, the turbine vane having a hollow interior; an impingement baffle assembly secured to the outer band so as to define an impingement cavity in coopera
A turbine nozzle segment includes: an arcuate outer band segment; an airfoil-shaped turbine vane extending radially inward from the outer band segment, the turbine vane having a hollow interior; an impingement baffle assembly secured to the outer band so as to define an impingement cavity in cooperation with the outer band segment, wherein the impingement baffle assembly has at least one impingement hole formed therein which is arranged to direct cooling air at the outer band segment; and at least one impingement insert having at least one impingement hole formed therein disposed in the interior of the turbine vane, the impingement insert mating with an opening in the impingement baffle assembly such that the impingement baffle is isolated from direct fluid communication with the impingement cavity.
대표청구항▼
1. A turbine nozzle segment comprising: an arcuate outer band segment;an airfoil-shaped turbine vane extending radially inward from the outer band segment, the turbine vane having a hollow interior;an impingement baffle assembly secured to the outer band so as to define an impingement cavity in coop
1. A turbine nozzle segment comprising: an arcuate outer band segment;an airfoil-shaped turbine vane extending radially inward from the outer band segment, the turbine vane having a hollow interior;an impingement baffle assembly secured to the outer band so as to define an impingement cavity in cooperation with the outer band segment, wherein the impingement baffle assembly has at least one impingement hole formed therein which is arranged to direct cooling air at the outer band segment; andat least one impingement insert having at least one impingement hole formed therein disposed in the interior of the turbine vane, the at least one impingement insert mating with an opening in the impingement baffle assembly such that the at least one impingement insert is isolated from direct fluid communication with the impingement cavity;wherein the impingement baffle assembly includes a perimeter frame and an impingement baffle extending radially inward from the frame; andwherein the outer band segment includes a central portion, an arcuate, radially-outwardly-extending forward rail, and an arcuate, radially-outwardly-extending aft rail; andthe forward rail, the central portion, and the aft rail all terminate at a common side face on each lateral side of the outer band segment; andeach of the side faces of the outer band segment defines spaced-apart radially inner and outer rails with an open window therebetween that exposes the impingement cavity. 2. The turbine nozzle segment of claim 1 wherein each side face includes at least one seal slot formed therein configured to receive a spline seal. 3. The turbine nozzle segment of claim 2 wherein the impingement baffle assembly is brazed to the outer band. 4. The turbine nozzle segment of claim 1 wherein the frame includes a forward edge, an aft edge, and spaced-apart side edges, the forward edge mating with the forward rail of the outer band segment and the aft edge mating with the aft rail of the outer band segment. 5. The turbine nozzle segment of claim 1 further comprising forward and aft impingement inserts which are received in the interior of the turbine vane, and mate with forward and aft openings, respectively, of the impingement baffle assembly. 6. The turbine nozzle segment of claim 1 wherein the impingement insert has an airfoil cross-sectional shape. 7. The turbine nozzle segment of claim 1 wherein the impingement baffle has a plurality of impingement holes formed therein. 8. The turbine nozzle segment of claim 1 wherein the impingement insert is brazed to the impingement baffle. 9. The turbine nozzle segment of claim 1 further comprising an arcuate inner band segment disposed at a radially inner end of the turbine vane. 10. A turbine nozzle assembly for a gas turbine engine, comprising: a plurality of turbine nozzle segments arranged in an annular array, each turbine nozzle segment comprising: an arcuate outer band segment;an airfoil-shaped turbine vane extending radially inward from the outer band segment, the turbine vane having a hollow interior;an impingement baffle assembly secured to the outer band so as to define an impingement cavity in cooperation with the outer band segment, wherein the impingement baffle assembly has at least one impingement hole formed therein which is arranged to direct cooling air at the outer band segment; andat least one impingement insert having at least one impingement hole formed therein disposed in the interior of the turbine vane, the at least one impingement insert mating with an opening in the impingement baffle assembly such that the at least one impingement insert is isolated from direct fluid communication with the impingement cavity; andan annular supporting structure surrounding the turbine nozzle segments;wherein the impingement baffle assembly includes a perimeter frame and an impingement baffle extending radially inward from the frame; andwherein each outer band segment includes a central portion, an arcuate, radially-outwardly-extending forward rail, and an arcuate, radially-outwardly-extending aft rail; andthe forward rail, the central portion, and the aft rail all terminate at a common side face on each lateral side of the outer band segment;and each of the side faces of each outer band segment defines spaced-apart radially inner and outer rails with an open window therebetween that exposes the impingement cavity. 11. The turbine nozzle assembly of claim 10 wherein each side face includes at least one seal slot formed therein configured to receive a spline seal. 12. The turbine nozzle assembly of claim 10 wherein each frame includes a forward edge, an aft edge, and spaced-apart side edges, the forward edge mating with the forward rail of the associated outer band segment and the aft edge mating with the aft rail of the associated outer band segment. 13. The turbine nozzle assembly of claim 10 further comprising forward and aft impingement inserts which are received in the interior of the turbine vane, and mate with forward and aft openings, respectively, of the impingement baffle assembly. 14. The turbine nozzle assembly of claim 10 wherein each opening has an airfoil cross-sectional shape. 15. The turbine nozzle assembly of claim 10 wherein each impingement baffle has a plurality of impingement holes formed therein. 16. The turbine nozzle assembly of claim 10 wherein the impingement baffle assembly is brazed to the outer band. 17. The turbine nozzle assembly of claim 10 wherein each opening is brazed to the associated impingement baffle. 18. The turbine nozzle assembly of claim 10 further comprising an arcuate inner band segment disposed at a radially inner end of each turbine vane.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (17)
Steven Sebastian Burdgick, Apparatus and methods for impingement cooling of a side wall of a turbine nozzle segment.
Yufeng Phillip Yu ; Gary Michael Itzel ; Waylon Willard Webbon ; Radhakrishna Bagepalli ; Steven Sebastian Burdgick ; Iain Robertson Kellock, Support pedestals for interconnecting a cover and nozzle band wall in a gas turbine nozzle segment.
Cunha Francisco J. (Schenectady NY) DeAngelis David A. (Voorheesville NY) Brown Theresa A. (Clifton Park NY) Chopra Sanjay (Albany NY) Correia Victor H. S. (New Labanon NY) Predmore Daniel R. (Clifto, Turbine stator vane segments having combined air and steam cooling circuits.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.