Nozzle arrangement and method of making the same

Abstract

A nozzle arrangement is disclosed herein for use with a supersonic jet engine that is configured to produce a plume of exhaust gases. The nozzle arrangement includes, but is not limited to, a nozzle having a trailing edge and a plug body partially positioned within the nozzle. The plug body has an expansion surface and a compression surface downstream of the expansion surface. A protruding portion of the plug body extends downstream of the trailing edge for a length greater than a conventional plug body length. The plug body is configured to shape the exhaust gases to flow substantially parallel to a free stream of air flowing off of the trailing edge of the nozzle and to cause the plume of exhaust gases to isentropically turn the free stream of air to move in a direction parallel to a longitudinal axis of the plug body.

What is claimed is: 
     
       1. A nozzle arrangement for use with a supersonic jet engine configured to produce a plume of exhaust gases when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed, the nozzle arrangement comprising:
 a nozzle configured to exhaust the plume of exhaust gases, the nozzle having a trailing edge; and 
 a plug body partially positioned within the nozzle and coaxially aligned with the nozzle, the plug body having an expansion surface and a compression surface downstream of the expansion surface, a protruding portion of the plug body extending downstream of the trailing edge, the protruding portion of the plug body having a concave surface proximate a terminus of the plug body, the plug body having contours and dimensions configured to shape the plume of exhaust gases such that the plume of exhaust gases flows substantially parallel to a direction of a free stream of air flowing off of the trailing edge of the nozzle proximate the trailing edge of the nozzle when the supersonic jet engine is operating at the predetermined power setting and moving at the predetermined Mach speed and has further contours and dimensions that are configured to cause the plume of exhaust gases to isentropically turn the free stream of air flowing off of the trailing edge of the nozzle at a location downstream of the trailing edge of the nozzle such that the free stream of air flowing off of the trailing edge moves in a direction parallel to a longitudinal axis of the plug body when the supersonic jet engine is operating at the predetermined power setting and moving at the predetermined Mach speed. 
 
     
     
       2. The nozzle arrangement of  claim 1 , wherein the compression surface comprises an isentropic compression surface. 
     
     
       3. The nozzle arrangement of  claim 1 , wherein a portion of the expansion surface is upstream of the trailing edge of the nozzle. 
     
     
       4. The nozzle arrangement of  claim 1 , wherein the plug body is configured to cause the plume of exhaust gases to isentropically turn the free stream of air flowing off of the trailing edge of the nozzle to the direction parallel to the longitudinal axis of the plug body at a location downstream of a trailing edge of the plug body. 
     
     
       5. The nozzle arrangement of  claim 1 , wherein the trailing edge of the nozzle is substantially axisymmetric and wherein the trailing edge of the nozzle and the expansion surface of the plug body define an annular outlet of the nozzle. 
     
     
       6. The nozzle arrangement of  claim 1 , wherein the expansion surface and the compression surface are contiguous with one another. 
     
     
       7. The nozzle arrangement of  claim 6 , wherein a surface of the plug body is devoid of discrete discontinuities in a region where the expansion surface transitions into the compression surface. 
     
     
       8. A nozzle arrangement for use with a supersonic jet engine configured to produce a plume of exhaust gases when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed, the nozzle arrangement comprising:
 a nozzle configured to exhaust the plume of exhaust gases, the nozzle having a trailing edge; 
 a plug body partially positioned within the nozzle and coaxially aligned with the nozzle; and 
 a bypass wall disposed between the nozzle and the plug body configured to direct a bypass airflow out of the nozzle, the plug body having an expansion surface and a compression surface downstream of the expansion surface, a protruding portion of the plug body extending downstream of the trailing edge, the protruding portion of the plug body having a concave surface proximate a terminus of the plug body, the plug body having contours and dimensions configured to shape the plume of exhaust gases and the bypass airflow such that the plume of exhaust gases and the bypass airflow flow substantially parallel to a direction of a free stream of air flowing off of the trailing edge of the nozzle proximate the trailing edge of the nozzle when the supersonic jet engine is operating at the predetermined power setting and moving at the predetermined Mach speed and has further contours and dimensions that are configured to cause the plume of exhaust gases and the bypass airflow to isentropically turn the free stream of air flowing off of the trailing edge of the nozzle at a location downstream of the trailing edge of the nozzle such that the free stream of air flowing off of the trailing edge moves in a direction parallel to a longitudinal axis of the plug body when the supersonic jet engine is operating at the predetermined power setting and moving at the predetermined Mach speed. 
 
     
     
       9. The nozzle arrangement of  claim 8 , wherein the compression surface comprises an isentropic compression surface. 
     
     
       10. The nozzle arrangement of  claim 8 , wherein a portion of the expansion surface is upstream of the trailing edge of the nozzle. 
     
     
       11. The nozzle arrangement of  claim 8 , wherein the plug body is configured to cause the plume of exhaust gases and the bypass airflow to isentropically turn the free stream of air flowing off of the trailing edge of the nozzle to the direction parallel to the longitudinal axis of the plug body at a location downstream of a trailing edge of the plug body. 
     
     
       12. The nozzle arrangement of  claim 8 , wherein the trailing edge of the nozzle is substantially axisymmetric and wherein the trailing edge of the nozzle and the expansion surface of the plug body define an annular outlet of the nozzle. 
     
     
       13. The nozzle arrangement of  claim 8 , wherein the expansion surface and the compression surface are contiguous with one another. 
     
     
       14. The nozzle arrangement of  claim 13 , wherein a surface of the plug body is devoid of discrete discontinuities in a region where the expansion surface transitions into the compression surface. 
     
     
       15. A method of making a nozzle arrangement for use with a supersonic jet engine configured to produce a plume of exhaust gases when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed, the nozzle arrangement method comprising:
 providing a nozzle configured to exhaust the plume of exhaust gases, the nozzle having a trailing edge, and a plug body having an expansion surface and a compression surface downstream the expansion surface; 
 positioning the plug body with respect to the nozzle such that the plug body is partially positioned within the nozzle and coaxially aligned therewith and such that a protruding portion of the plug body extends downstream of the trailing edge, 
 wherein the protruding portion of the plug body has a concave surface proximate a terminus of the plug body, 
 wherein the plug body has contours and dimensions configured to shape the plume of exhaust gases such that the plume of exhaust gases flows substantially parallel to a direction of a free stream of air flowing off of the trailing edge of the nozzle proximate the trailing edge of the nozzle when the supersonic jet engine is operating at the predetermined power setting and moving at the predetermined Mach speed, and 
 wherein the plug body has further contours and dimensions that are configured to cause the plume of exhaust gases to isentropically turn the free stream of air flowing off of the trailing edge of the nozzle at a location downstream of the trailing edge of the nozzle such that the free stream of air flowing off of the trailing edge moves in a direction parallel to a longitudinal axis of the plug body when the supersonic jet engine is operating at the predetermined power setting and moving at the predetermined Mach speed. 
 
     
     
       16. The method of  claim 15 , wherein providing the plug body having an expansion surface and a compression surface downstream of the expansion surface comprises providing a plug body wherein the compression surface is an isentropic compression surface. 
     
     
       17. The method of  claim 15 , wherein providing the plug body having an expansion surface and the a compression surface downstream of the expansion surface comprises providing a plug body wherein the expansion surface is contiguous with the compression surface. 
     
     
       18. The method of  claim 17 , wherein providing the plug body having wherein the expansion surface that is contiguous with the compression surface comprises providing a plug body wherein the plug body lacks lacking any discrete discontinuities between the expansion surface and the compression surface. 
     
     
       19. A method of making a nozzle arrangement for use with a supersonic jet engine configured to produce a plume of exhaust gases when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed, the nozzle arrangement method comprising:
 providing a nozzle configured to exhaust the plume of exhaust gases, the nozzle having a trailing edge, and a plug body having an expansion surface and a compression surface downstream the expansion surface; 
 positioning the plug body with respect to the nozzle such that the plug body is partially positioned within the nozzle and coaxially aligned therewith and such that a protruding portion of the plug body extends downstream of the trailing edge; 
 providing a bypass wall and positioning the bypass wall between the nozzle and the plug body, 
 wherein the protruding portion of the plug body has a concave surface proximate a terminus of the plug body, 
 wherein the plug body has contours and dimensions configured to shape the plume of exhaust gases and a bypass flow such that the plume of exhaust gases and the bypass flow both flow substantially parallel to a direction of a free stream of air flowing off of the trailing edge of the nozzle proximate the trailing edge of the nozzle when the supersonic jet engine is operating at the predetermined power setting and moving at the predetermined Mach speed, and 
 wherein the plug body has further contours and dimensions that are configured to cause the plume of exhaust gases and the bypass flow to isentropically turn the free stream of air flowing off of the trailing edge of the nozzle at a location downstream of the trailing edge of the nozzle such that the free stream of air flowing off of the trailing edge moves in a direction parallel to a longitudinal axis of the plug body when the supersonic jet engine is operating at the predetermined power setting and moving at the predetermined Mach speed.