[go: up one dir, main page]

Kim et al., 2019 - Google Patents

Acoustic damping characterization of a double-perforated liner in an aero-engine combustor

Kim et al., 2019

Document ID
9833620186994813595
Author
Kim D
Jung S
Park H
Publication year
Publication venue
Journal of Mechanical Science and Technology

External Links

Snippet

Double-perforated liners are widely used in gas turbine combustors because of their improved thermal load characteristics and broader acoustic damping compared with single- layer perforations. The present study examines the absorption of normal-incidence acoustic …
Continue reading at link.springer.com (other versions)

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING ENGINES OR PUMPS
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies
    • Y02T50/67—Relevant aircraft propulsion technologies
    • Y02T50/671—Measures to reduce the propulsor weight
    • Y02T50/672—Measures to reduce the propulsor weight using composites
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING ENGINES OR PUMPS
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING ENGINES OR PUMPS
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures

Similar Documents

Publication Publication Date Title
Bothien et al. A novel damping device for broadband attenuation of low-frequency combustion pulsations in gas turbines
Dupere et al. The use of Helmholtz resonators in a practical combustor
Zhao et al. Tuned passive control of acoustic damping of perforated liners
Lepers et al. Investigation of thermoacoustic stability limits of an annular gas turbine combustor test-rig with and without Helmholtz-resonators
Rupp et al. The use of perforated damping liners in aero gas turbine combustion systems
Bothien et al. Impact of density discontinuities on the resonance frequency of Helmholtz resonators
Du et al. Intense vibration mechanism analysis and vibration control technology for the combustion chamber of a liquid rocket engine
Kim et al. Acoustic damping characterization of a double-perforated liner in an aero-engine combustor
Camporeale et al. Numerical simulation of the acoustic pressure field in an annular combustion chamber with helmholtz resonators
Guzman-Inigo et al. Sensitivity of the acoustics of short circular holes with bias flow to inlet edge geometries
Kim et al. Design of acoustic liner in small gas turbine combustor using one-dimensional impedance models
Andreini et al. Experimental investigation on effusion liner geometries for aero-engine combustors: evaluation of global acoustic parameters
Jayatunga et al. Absorption of normal-incidence acoustic waves by double perforated liners of industrial gas turbine combustors
Kim et al. Geometric and number effect on damping capacity of Helmholtz resonators in a model chamber
Han et al. Effect of the diffuser on the inlet acoustic boundary in combustion-acoustic coupled oscillation
Bothien et al. A novel damping device for broadband attenuation of low-frequency combustion pulsations in gas turbines
Yang et al. An analysis and optimum design of the weak coupling between cavities for broadband sound absorption of parallel Helmholtz resonators
Forte et al. Effect of burner and resonator impedances on the acoustic behavior of annular combustion chambers
Ikwubuo et al. Experimental Investigation of Acoustic Characteristics of Boundary Condition for a Combustor
Xu et al. Suppression of combustion instabilities in a premixed swirl combustor with acoustic liner
Zhu et al. Theoretical and experimental investigations on the acoustic absorptions of baffled injectors
Rupp et al. The use of perforated damping liners in aero gas turbine combustion systems
Tran et al. Passive control of the inlet acoustic boundary of a swirled turbulent burner
Ikwubuo et al. Experimental investigation of acoustic characteristic on orifice shaped with bias flow
Liu et al. Experimental study on the mid-frequency sound absorption performance of multiple aperture dual perforated plates traversed by bias flow