IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0200616
(2005-08-10)
|
등록번호 |
US-7543452
(2009-07-01)
|
발명자
/ 주소 |
- Reba, Ramons Andris
- Wake, Brian Ernest
- Narayanan, Satish
- Maeder, Thierry
|
출원인 / 주소 |
- United Technologies Corporation
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
9 인용 특허 :
28 |
초록
▼
A nozzle for a gas turbine engine is provided with undulations on a core and/or fan exhaust flow nozzle. An annular wall defines a fluid flow passage and includes a base portion and an adjoining exit portion. The base portion is typically generally frustoconical in shape and includes an arcuate cont
A nozzle for a gas turbine engine is provided with undulations on a core and/or fan exhaust flow nozzle. An annular wall defines a fluid flow passage and includes a base portion and an adjoining exit portion. The base portion is typically generally frustoconical in shape and includes an arcuate contour in an axial direction. The exit portion includes undulations in a generally radial direction that provide lobes and troughs each respectively including trailing edges. One of the lobe and trough trailing edges are recessed from the other of the lobe and trough trailing edges in a generally axial direction. The other of the lobe and trough trailing edges form apexes with the apexes provided on tabs. The troughs extend radially inward in the axial direction towards the trough trailing edges.
대표청구항
▼
What is claimed is: 1. A nozzle comprising: an annular wall defining a fluid flow passage and including a base portion and an adjoining exit portion, the exit portion including undulations in a generally radial direction that provide lobes and troughs in the annular wall that each respectively incl
What is claimed is: 1. A nozzle comprising: an annular wall defining a fluid flow passage and including a base portion and an adjoining exit portion, the exit portion including undulations in a generally radial direction that provide lobes and troughs in the annular wall that each respectively including trailing edges, one of the lobe and trough trailing edges in the annular wall recessed from the other of the lobe and trough trailing edges in the annular wall in a generally axial direction, the other of the lobe and trough trailing edges in the annular wall form apexes with the apexes provided on tabs, and troughs extending radially inward in an axial direction towards the trough trailing edges. 2. A nozzle according to claim 1, wherein the troughs provide the tabs with the trailing edges that form the apexes. 3. A nozzle according to claim 2, wherein the lobe trailing edges include arcuate recesses. 4. A nozzle according to claim 1, wherein the tabs are v-shaped forming a generally sharp point providing the apex. 5. A nozzle comprising: an annular wall defining a fluid flow passage and including a base portion and an adjoining exit portion, the exit portion including undulations in a generally radial direction that provide lobes and troughs each respectively including trailing edges, one of the lobe and trough trailing edges recessed from the other of the lobe and trough trailing edges in a generally axial direction, the other of the lobe and trough trailing edges form apexes with the apexes provided on tabs, and troughs extending radially inward in an axial direction towards the trough trailing edges; and wherein the base portion includes a contour with an imaginary surface extending axially in the direction of the contour, the lobes extending radially outwardly of the imaginary surface and the troughs extending radially inwardly of the imaginary surface. 6. A nozzle according to claim 1, wherein the lobes are recessed from the troughs in the generally axial direction. 7. A nozzle comprising: an annular wall defining a fluid flow passage and including a base portion and an adjoining exit portion, the exit portion including undulations in a generally radial direction that provide lobes and troughs each respectively including trailing edges, one of the lobe and trough trailing edges recessed from the other of the lobe and trough trailing edges in a generally axial direction, the other of the lobe and trough trailing edges form apexes with the apexes provided on tabs, and troughs extending radially inward in an axial direction towards the trough trailing edges; and wherein the troughs are recessed from the lobes in the generally axial direction, the lobes extending radially outwardly at an angle approximately between 0 and 26 degrees. 8. A nozzle according to claim 7, wherein the lobes are radially spaced from the imaginary surface at approximately a height, the lobes breaking the imaginary surface and defining a distance, the height divided by the width defining a ratio of approximately 1 or less. 9. A nozzle according to claim 1, wherein a plane includes an axis of the nozzle, one of the apexes lying in the plane, and an edge of the tab that includes the one of the apexes at an angle relative to the plane providing a tab platform. 10. A nozzle according to claim 1, wherein the one of the lobe and trough trailing edges being recessed from the other of the lobe and trough trailing edges in the generally axial direction forms an arcuate contour. 11. A nozzle comprising: an annular wall defining a fluid flow passage and including a base portion and an adjoining exit portion, the exit portion including undulations in a generally radial direction that provide lobes and troughs each respectively including trailing edges, one of the lobe and trough trailing edges recessed from the other of the lobe and trough trailing edges in a generally axial direction, the other of the lobe and trough trailing edges form apexes with the apexes provided on tabs, and troughs extending radially inward in an axial direction towards the trough trailing edges; and wherein the lobes and troughs provide a sinusoidal circumferential contour. 12. A nozzle according to claim 1, wherein the tabs include a tab contour in the generally axial direction, the tabs extending radially inwardly near the apexes to provide a tab penetration angle relative to the tab contour. 13. A nozzle according to claim 12, wherein the tab contour is parabolic. 14. A nozzle according to claim 1, wherein the nozzle includes approximately between 6 to 12 tabs and 6 to 12 lobes. 15. A gas turbine engine comprising: a fan exhaust nozzle arranged about a core exhaust nozzle, and a central body positioned within the core exhaust nozzle; one of the nozzles including an annular wall defining a fluid flow passage and including a base portion and an adjoining exit portion, the exit portion including undulations in a generally radial direction that provide lobes and troughs each respectively including trailing edges, one of the lobe and trough trailing edges recessed from the other of the lobe and trough trailing edges in a generally axial direction, the other of the lobe and trough trailing edges form apexes with the apexes provided on tabs, and troughs extending radially inward in an axial direction towards the trough trailing edges. 16. The gas turbine engine according to claim 15, wherein the one of the nozzles is the core exhaust nozzle. 17. The gas turbine engine according to claim 16, wherein the apexes extend beyond a terminal end of the fan exhaust nozzle. 18. The gas turbine engine according to claim 15, wherein the one of the nozzles is the fan exhaust nozzle. 19. The gas turbine engine according to claim 18, wherein the other nozzle includes a second annular wall defining a second fluid flow passage and includes a second base portion and a second adjoining exit portion, the second exit portion including second undulations in the generally radial direction that provide second lobes and second troughs each respectively including second trailing edges, one of the second lobe and trough trailing edges recessed from the other of the second lobe and trough trailing edges in the generally axial direction, the other of the second lobe and trough trailing edges form second apexes with the second apexes provided on second tabs, and second troughs extending radially inward in an axial direction towards the second trough trailing edges. 20. The gas turbine engine according to claim 19, wherein a number of the tabs and second tabs are equal, the lobes and second lobes in radial alignment with one another.
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