초록 ▼

Nozzle exit configurations and associated systems and methods are disclosed. An aircraft system in accordance with one embodiment includes a jet engine exhaust nozzle having an internal flow surface and an exit aperture, with the exit aperture having a perimeter that includes multiple projections ex

Nozzle exit configurations and associated systems and methods are disclosed. An aircraft system in accordance with one embodiment includes a jet engine exhaust nozzle having an internal flow surface and an exit aperture, with the exit aperture having a perimeter that includes multiple projections extending in an aft direction. Aft portions of individual neighboring projections are spaced apart from each other by a gap, and a geometric feature of the multiple can change in a monotonic manner along at least a portion of the perimeter. Projections near a support pylon and/or associated heat shield can have particular configurations, including greater flow immersion than other projections.

대표청구항 ▼

1. An aircraft system, comprising: a pylon having a first side, a second side facing opposite the first side, and a heat shield having a first edge proximate to the first side of the pylon and a second edge proximate to the second side of the pylon; anda jet engine exhaust nozzle carried by the pylo

1. An aircraft system, comprising: a pylon having a first side, a second side facing opposite the first side, and a heat shield having a first edge proximate to the first side of the pylon and a second edge proximate to the second side of the pylon; anda jet engine exhaust nozzle carried by the pylon and having an internal flow surface adjacent a hot exhaust flow path, the internal flow surface having an exit aperture with a perimeter that includes multiple projections extending in an aft direction and circumferentially spaced about the perimeter, with a geometric feature of the multiple projections changing in a monotonic manner along at least a portion of the perimeter, wherein a first projection nearest the first side of the pylon and a second projection nearest the second side of the pylon are both oriented inwardly into the flow path by a greater amount than the remaining projections, and wherein at least a portion of the first projection is positioned circumferentially outwardly from the first edge of the heat shield and at least a portion of the second projection is positioned circumferentially outwardly from the second edge of the heat shield. 2. The system of claim 1 wherein at least a portion of the first projection is positioned circumferentially outwardly from the first side of the pylon and at least a portion of the second projection is positioned circumferentially outwardly from the second side of the pylon. 3. The system of claim 1 wherein: each of the first and second projections has a generally triangular shape with a root and a tip;the root of the first projection has a first orientation relative to the first side of the pylon; andthe root of the second projection has a second orientation relative to the second side of the pylon that generally mirrors the first orientation. 4. The system of claim 3 wherein the root of the first projection is offset from the first side of the pylon by a first value in a first direction, and wherein the root of the second projection is offset from the second side of the pylon by a second value generally the same as the first value in a second direction generally opposite the first direction. 5. The system of claim 4 wherein the root of the first projection is offset from the first side of the pylon by a first angle in a first direction, and wherein the root of the second projection is offset from the second side of the pylon by a second angle generally the same as the first angle in a second direction generally opposite the first direction. 6. The system of claim 4 wherein the root of the first projection is offset from the first side of the pylon by a first distance in a first direction, and wherein the root of the second projection is offset from the second side of the pylon by a second distance generally the same as the first distance in a second direction generally opposite the first direction. 7. The system of claim 3 wherein the tip of the first projection is offset from the first side of the pylon by a first value in a first direction, and wherein the tip of the second projection is offset from the second side of the pylon by a second value generally the same as the first value in a second direction generally opposite the first direction. 8. The system of claim 3 wherein the tip of the first projection is circumferentially aligned with the first side of the pylon and wherein the tip of the second projection is circumferentially aligned with the second side of the pylon. 9. The system of claim 1 wherein the first projection is inclined radially inwardly into the flow by a greater amount than is a neighboring projection located circumferentially outwardly from the first projection. 10. The system of claim 1 wherein the first projection has a greater axial extent than does a neighboring projection located circumferentially outwardly from the first projection. 11. The system of claim 1 wherein the exhaust nozzle includes a fan flow path positioned radially outwardly from the internal flow surface. 12. A method for operating an aircraft engine, comprising: directing a flow of hot exhaust gas from an aircraft engine through an exhaust nozzle exit aperture, the aperture having a perimeter with axially extending projections arranged around the perimeter, and with a geometric feature of the projections changing in a monotonic manner along at least a portion of the perimeter; andcontrolling the flow of hot exhaust gas near a pylon supporting the engine by directing the flow adjacent to first and second projections located at least partially outwardly from and nearest to first and second oppositely facing sides of the pylon, the first and second projections being oriented inwardly into the flow by a greater amount than are the remaining projections, wherein the pylon includes a heat shield having a first edge proximate to the first side of the pylon and a second edge proximate to the second side of the pylon, and wherein at least a portion of the first projection is positioned circumferentially outwardly from the first edge of the heat shield and at least a portion of the second projection is positioned circumferentially outwardly from the second edge of the heat shield. 13. The method of claim 12 wherein controlling the flow includes at least restricting the hot flow from passing adjacent to at least one of the sides of the pylon. 14. The method of claim 12 wherein controlling the flow includes entraining air from an adjacent flow of cooler bypass air by at a greater rate near the pylon than at other circumferential locations around the nozzle exit aperture. 15. The method of claim 12 wherein each of the first and second projections has a generally triangular shape with a tip and an inner and outer root, and wherein directing the hot flow includes directing the flow adjacent to the outer root of the first projection that is located circumferentially outwardly from the first side of the pylon, and directing the flow adjacent to the outer root of the second projection that is located circumferentially outwardly from the second side of the pylon. 16. The method of claim 12 wherein controlling the flow includes increasing an axial vorticity component of the flow near the pylon or the heat shield compared with an axial vorticity component of the flow at other circumferential locations around the exit aperture. 17. The method of claim 12 wherein controlling the flow includes controlling an amount of heating at the sides of the pylon. 18. A method for designing an aircraft system, comprising: sizing an engine pylon for carrying an aircraft engine and exhaust nozzle having a hot exhaust flow path;configuring a set of multiple projections extending aft around an exit aperture of the nozzle to have a geometric feature that changes in a monotonic manner along at least a portion of a perimeter of the exit aperture, the projections including a first projection positioned nearest a first side of the pylon and a second projection positioned nearest a second side of the pylon facing generally opposite the first side; andconfiguring a heat shield positioned to protect the pylon from exhaust gases, wherein configuring at least one of the heat shield and the set of projections is based at least in part on expected results of configuring the other of the heat shield and the set of projections, and wherein configuring at least one of the heat shield and the set of projections includes configuring at least a portion of the first projection to be circumferentially outwardly from a first edge of the heat shield positioned proximate to the first side of the pylon, and at least a portion of the second projection to be circumferentially outwardly from a second edge of the heat shield positioned proximate to the first side of the pylon. 19. The method of claim 18 wherein configuring multiple projections includes configuring the first and second projections to be immersed in the exhaust flow path to a greater degree than the remaining projections. 20. The method of claim 19 wherein configuring the first and second projections includes configuring the first and second projections to be angled inwardly into the flow path by a greater degree than the remaining projections. 21. The method of claim 18 wherein each of the first and second projections includes a tip and a root, and wherein configuring the heat shield includes aligning edges of the heat shield to be offset inwardly from the tips of the first and second projections. 22. The method of claim 18 wherein each of the first and second projections includes a tip and a root, and wherein configuring the heat shield includes aligning edges of the heat shield to be circumferentially aligned with the tips of the first and second projections.