Aerospike Engine, Jeff Scott, Fall 1999. This paper gives an extensive review of the various altitude compensating nozzle designs. Confusingly, the term "plug nozzle" may also be used to refer to an entirely different class of engine nozzles, the aerospikes. In theory the aerospike should look roughly like a lance, with a wide base and long tapering forebody. However, the "spike" portion can be cut off with only minor effects on performance, leaving just the base section. This looks very similar to a common drain plug or bung, and leads to widespread use of the term "plug nozzle" for this design as well. When water is supplied to the hose, it flows through the nozzle body to the opening, where it would normally flow straight forward in a stream. Just after leaving the opening it encounters the plug, which deflects the water sideways through an angle. After travelling a short distance the water encounters the outside of the nozzle opening, which deflects it forward again. This two-step process causes the water to be ejected in a ring-shaped pattern, which causes less water to strike any one location, and thereby reduces erosion while also making it easier to water larger areas. Weight and cooling are typical concerns with aircraft plug nozzles. [7] A plug nozzle design evaluated at the National Gas Turbine Establishment [8] was rejected for the Concorde engine due to the weight penalty from the required variable features and concerns about adequate plug cooling during reheat operation. [9] Archived copy". Archived from the original on 2018-07-26 . Retrieved 2018-07-25. {{ cite web}}: CS1 maint: archived copy as title ( link)

Propelling nozzles for subsonic aircraft have used a center-body/bullet/cone to give the nozzle exit area required to set an axial compressor running-line correctly on its map. The first operational German turbojet engines with axial compressors, the Jumo 004 and BMW 003, needed a different exhaust nozzle areas for running properly at each of the operating regimes: start/idle, climb, high speed, high altitude. [11] A nozzle with a fore/aft-translating "bullet" restrictive body in the center was chosen for each design. It provided area control with relatively simple actuation and matched the annular shape of the turbine exhaust. Plug nozzle model tests have shown reduced noise levels compared to traditional con-di nozzles. [10] The stopper is mainly used for opening and closing the flow control of the tundish. it is installed in the tundish, and the flow rate of the molten steel entering the casting mold is adjusted by controlling the position of the stopper head to the tundish nozzle. The submerged entry nozzle is to protect the molten steel from being oxidized by ambient air when flowing from tundish into the casting mold, and to uniformly distribute the molten steel into the casting mold and control the flow state of the molten steel. Archived copy" (PDF). Archived from the original (PDF) on 2015-10-01 . Retrieved 2018-07-25. {{ cite web}}: CS1 maint: archived copy as title ( link)

Publications

Stitt, Leonard E. (May 1, 1990). "Exhaust Nozzles for Propulsion Systems with Emphasis on Supersonic Cruise Aircraft". ntrs.nasa.gov. p.31. Archived from the original on October 5, 2021 . Retrieved July 25, 2018. A Case Study By Aerospatiale And British Aerospace On The Concorde,Rech and Leyman, AIAA Professional Study Series, p. 6-10

The ladle shroudis a product that connects the steel ladle and the tundish. When the molten steel casting from steel ladle into the tundish through the ladle shroud, it can prevent the molten steel from oxidation and splashing.

Connect

Plug nozzles belong to a class of altitude compensating nozzles, much like the aerospike, which, unlike traditional designs, maintains its efficiency at a wide range of altitudes. [1] In aircraft and missiles [ edit ] Sectioned Jumo 004 exhaust nozzle, showing the Zwiebel restrictive body Tupolev Tu-114' Gordon, Komissarov and Rigmant, Schiffer Publishing Ltd. 2015, ISBN 978-0-7643-4894-5, p.188

Stitt, Leonard E. (May 1990). "Exhaust Nozzles for Propulsion Systems With Emphasis on Supersonic Cruise Aircraft" (PDF). Reference Publication 1235. NASA. Archived (PDF) from the original on 17 May 2010 . Retrieved 14 July 2012. (42.1 Mb) Aukerman, Carl A. (August 1, 1991). "Plug nozzles: The ultimate customer driven propulsion system". Archived from the original on October 5, 2021 . Retrieved July 25, 2018– via ntrs.nasa.gov.