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.
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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.
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.
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.
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.
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This application has an isentropic compression surface and As illustrated in the embodiment presented in FIG. 5, compression surface 138 has a concave configuration. See also, FIGS. 8 and 10.
Accordingly, for a known Mach speed of the exhaust gases traveling past trailing end 134, a Mach line 154 will propagate off of trailing end 134 at angle β. Using both angle β and the location of the arrow heads, the location of trailing end 134 can be determined by positioning an end of each Mach line 154 on each arrowhead 152 and, looking in an upstream direction, determining where the Mach lines intersect. That point of intersection is the location where trailing end 134 will be located. Once the location of trailing end 134 is determined, the overall length of body plug 128 can be determined.
Next, a desired curvature is selected for the turning of the free stream. This curvature is represented by phantom line 155 and is selected by the nozzle designer. One criteria may be to choose a curvature that will result in an isentropic change in direction of the free stream. Once the desired curvature is selected, the contours and configuration of plug body 128 can be determined using Method of Characteristics. When utilizing Methods of Characteristics, phantom line 155 is considered to be a boundary condition and the contours and configuration of plug body 128 is calculated by selecting a curvature for plug body 128 that will cause the exhaust gases to conform to phantom line 155. Other techniques such as the use of computational fluid dynamics software may also be utilized when determining the geometry of plug body 128.
At step 158, a cowl, a center body and a bypass splitter are provided. In some embodiments, the supersonic engine may not include a bypass. For such embodiments, this step would not include providing a bypass splitter. The cowl has a cowl lip. The center body has an apex, a first compression surface located downstream of the apex, and a second compression surface located downstream of the first compression surface.
At step 160, the center body is positioned with respect to the cowl such that the center body is coaxial with the cowl, a protruding portion of the center body extends upstream of the cowl lip for a length that is greater than a conventional spike length, and the second compression surface is spaced apart from the cowl lip such that the second compression surface and the cowl lip define an inlet.
At step 162, for supersonic engines that are configured with a bypass splitter, the bypass splitter is positioned between the cowl and the center body to form a bypass that is configured to receive air at a second predetermined mass flow rate when the supersonic jet engine is operating at the predetermined power setting and moving at the predetermined Mach speed.
When properly implemented, method steps 158-162 will yield an inlet arrangement where the protruding portion of the center body is configured to divert a flow of air that is located in a path of the inlet out of the path of the inlet such that a remaining flow of air that approaches and enters the inlet is not greater than the predetermined mass flow rate when the jet engine is operating at the predetermined power setting and moving at the predetermined Mach speed. For embodiments of the supersonic jet engine that include the bypass, the center body is configured to divert the flow of air that is located in the path of the inlet out of the path of the inlet such that the remaining flow of air approaching and entering the inlet is not greater than the first predetermined mass flow rate (i.e., the predetermined rate at which air is consumed by the turbo machinery of the supersonic jet engine) and the second predetermined mass flow rate (i.e., the rate at which the by-pass routes airflow around the turbo machinery) combined when the jet engine is operating at the predetermined power setting and moving at the predetermined Mach speed.
At step 166 a nozzle, a plug body, and a bypass wall are provided. In some embodiments, a bypass will not be utilized. For such embodiments, a bypass wall will not be provided. The nozzle is configured to exhaust the plume of exhaust gases and has a trailing edge oriented at a predetermined angle with respect to an axial direction of the nozzle. The plug body has an expansion surface and a compression surface downstream of the expansion surface.
At step 168, the plug body is positioned 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 for a length greater than a conventional plug body length.
At step 170, for embodiments that utilize a bypass, the bypass wall will be positioned between the nozzle and the plug body.
When properly implemented, method steps 166-170 will yield a nozzle arrangement wherein the protruding portion of the plug body will have a substantially circular cross-section along substantially an entire longitudinal length of the protruding portion of the plug body. The plug body will be configured to shape the plume of exhaust gases such that the plume of exhaust gases flows substantially parallel to a direction of the free stream of air flowing off of the trailing edge of the nozzle proximate the trailing edge of the nozzle and wherein the plug body is further 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. In embodiments that utilize a bypass, the plug body will be configured to cause the plume of exhaust gases and a 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 end of the plug body.
While at least one exemplary embodiment has been presented in the foregoing detailed description of the disclosure, it should be appreciated that a vast number of variations exist. It should also be appreciated that the exemplary embodiment or exemplary embodiments are only examples, and are not intended to limit the scope, applicability, or configuration of the invention in any way. Rather, the foregoing detailed description will provide those skilled in the art with a convenient road map for implementing an exemplary embodiment of the invention. It being understood that various changes may be made in the function and arrangement of elements described in an exemplary embodiment without departing from the scope of the disclosure as set forth in the appended claims.
Henne, Preston A., Howe, Donald C., Conners, Timothy R.
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