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Nozzles
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Image
Published: 30 November 2023
Fig. 8.8. Bank of spray nozzles. Reprinted with permission from Ref 8
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Image
Published: 01 March 2002
Fig. 5.11 Investment-cast gas turbine engine. (a) Polycrystalline integral nozzles, and (b) integral rotors
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Image
in Aerospace Applications—Example Fatigue Problems
> Fatigue and Durability of Metals at High Temperatures
Published: 01 July 2009
Fig. 10.13 Near-term fix to prevent aerodynamic excitation of preburner fuel nozzles in Space Shuttle Main Engines by inserting spacers to limit nozzle tip displacement
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Book Chapter
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270126
EISBN: 978-1-62708-301-0
... nozzle was also damaged, and based on its microstructure, came very close to melting. Investigators determined that the burner was mounted backwards, facing the compressor rather than the turbine. They also recommended a redesign to prevent the fuel nozzle from being reversed. fuel nozzles...
Abstract
A test flight was cut short after a fire warning came on indicating a problem with one of the four engines on an aircraft. A visual examination following the precautionary landing revealed several burned hoses, a melted bolt, and fuel leaking from the base of the main burner. The fuel nozzle was also damaged, and based on its microstructure, came very close to melting. Investigators determined that the burner was mounted backwards, facing the compressor rather than the turbine. They also recommended a redesign to prevent the fuel nozzle from being reversed.
Image
Published: 30 September 2023
Figure 9.18: Pressure or nozzle die for promoting hydrodynamic lubrication with soaps.
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Image
Published: 30 September 2023
Figure 9.20: Film thicknesses measured in drawing 0.3% C steel wire (nozzle length, 37 mm; reduction from 3.4 to 3.2 mm diameter with a Na-Ca-stearate soap) and calculated from a Bingham model ( η = 1.5 Pa-s).
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Image
Published: 30 September 2023
Figure 13.58: Methods of applying grinding fluids. (a) Simple fan-shaped nozzle; (b) large orifice nozzle with side guides; (c) large orifice nozzle with flow normal to wheel surface; (d) schematic of internal application of fluid, showing only three channels that are not to scale.
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Image
Published: 01 March 2002
Fig. 6.20 Exit nozzle of N-155 produced by tube spinning and subsequent explosive forming. (Dimensions in inches)
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Image
Published: 01 March 2002
Fig. 7.2 Gas atomization system for producing superalloy powder. (a) Nozzle detail (b) system
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Image
in Corrosion in Petroleum Refining and Petrochemical Operations[1]
> Corrosion in the Petrochemical Industry
Published: 01 December 2015
Fig. 46 Accelerated aqueous chloride corrosion below inlet nozzle of crude tower overhead condenser due to droplet impingement. Note partial loss of carbon steel baffles and localized corrosion along top of admiralty metal (C44300) tubes.
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Image
Published: 01 June 2016
Fig. 2.22 Influence of different powder injection points before the nozzle throat (20 mm, or 0.8 in., in a, c, and e versus 180 mm, or 7 in., in b, d, and f) on (a, b) particle heating, (c, d) acceleration, and (e, f) impact parameters within the window of deposition. The calculations were
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Image
Published: 01 June 2016
Fig. 3.15 Temperature and velocity development along the nozzle axis for nitrogen as the process gas (g) and two different copper particle sizes (5 and 25 µm), T 0 = 593 K, p 0 = 25 bar. The nozzle has an expansion ratio of 9. Source: Ref 3.2
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Image
Published: 01 June 2016
Fig. 3.19 Velocity contours of free gas jets at exits of (a) a trumpet-shaped nozzle and (b) a bell-shaped optimized nozzle design, as computed by FLUENT for nitrogen as the process gas at a gas inlet pressure of 3 MPa (435 psi) and a gas temperature of 320 °C (610 °F). Source: Ref 3.59
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Image
Published: 01 June 2016
Fig. 3.21 (a) Gas velocity versus the radial distance from the axis of the nozzle at the exit, computed by FLUENT for a method of characteristics nozzle. Throat diameter: 2.7 mm (0.1 in.), A/A* = 5.6, length of diverging section 130 mm (5 in.), with nitrogen as the process gas at p 0 = 4
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Image
Published: 01 October 2012
Fig. 9.28 Jet engine applications of titanium-matrix composites. (a) A nozzle actuator piston rod used on the Pratt & Whitney F119 engine for F-22 aircraft. The part is made of a Ti-6Al-2Sn-4Zr-2Mo alloy reinforced with SiC monofilaments that are 129 μm (5.1 mils) in diameter. The inset
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Image
Published: 01 October 2012
Fig. 11.18 Exhaust nozzle of an F414 engine on an F-18 E/F aircraft, showing the twelve sets of ceramic-matrix composite (CMC) flaps and seals. The white areas on the seals are a zirconia overcoat for mechanical fasteners. Over an order of magnitude increase in life has been obtained
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Image
in Failure of a Fuel Nozzle in an Aircraft Engine
> Failure Analysis of Engineering Structures: Methodology and Case Histories
Published: 01 October 2005
Fig. CH26.1 Damaged fuel nozzle
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Image
in Failure of a Fuel Nozzle in an Aircraft Engine
> Failure Analysis of Engineering Structures: Methodology and Case Histories
Published: 01 October 2005
Fig. CH26.2 Sketch of the nozzle assembly showing zone 1, Widmanstätten/basket weave microstructure (hardness, 320 HV); zone 2, spheroidized microstructure (hardness, 410 HV); and zone 3, martensitic microstructure (hardness, 520 HV)
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Image
in Aerospace Applications—Example Fatigue Problems
> Fatigue and Durability of Metals at High Temperatures
Published: 01 July 2009
Fig. 10.12 Injector nozzle element in a fuel preburner assembly showing location of the initiation and propagation of high-cycle fatigue cracks at the critical radius (point A )
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