2024
DOI: 10.1016/j.ast.2023.108857
|View full text |Cite
|
Sign up to set email alerts
|

Numerical investigation on film cooling and aerodynamic performance for gas turbine endwalls with upstream vane-type and cascade-type slots

Meng Feng,
Xingfu Dai,
Feng Zhang
et al.
Help me understand this report

Search citation statements

Order By: Relevance

Paper Sections

Select...
2

Citation Types

0
2
0

Year Published

2024
2024
2024
2024

Publication Types

Select...
7

Relationship

0
7

Authors

Journals

citations
Cited by 10 publications
(2 citation statements)
references
References 32 publications
0
2
0
Order By: Relevance
“…With the increasing performance requirements of combustion chambers and increasingly stringent emission regulations [1][2][3][4], gas turbine combustion chambers are required to operate at high temperature and high pressure [5][6][7][8][9], which usually leads to the occurrence of combustion instability [10][11][12][13][14][15][16][17]. The combustion instability phenomenon will be accompanied by pressure pulsation and exothermic pulsation in the flow field inside the combustion chamber [18][19][20][21], which leads to vibration of the combustion chamber components and affects the safe operation of the engine [22][23][24].…”
Section: Introductionmentioning
confidence: 99%
“…With the increasing performance requirements of combustion chambers and increasingly stringent emission regulations [1][2][3][4], gas turbine combustion chambers are required to operate at high temperature and high pressure [5][6][7][8][9], which usually leads to the occurrence of combustion instability [10][11][12][13][14][15][16][17]. The combustion instability phenomenon will be accompanied by pressure pulsation and exothermic pulsation in the flow field inside the combustion chamber [18][19][20][21], which leads to vibration of the combustion chamber components and affects the safe operation of the engine [22][23][24].…”
Section: Introductionmentioning
confidence: 99%
“…The afterburner is a critical component for thrust augmentation in military aircraft engines [1], enabling a substantial increase in the engine thrust from 60% to 70%. The airflow entering the afterburner is the exhaust gas from the main combustor in the aero-engine, which contains one-quarter less oxygen than pure air.…”
Section: Introductionmentioning
confidence: 99%