发动机进气道直流喷嘴防冰系统换热特性

doi:10.7527/S1000-6893.2026.33004

Abstract

Abstract:

To investigate the heat transfer characteristics of impinging jet and annular flow in the aero-engine inlet swirl nozzle anti-icing system， a numerical simulation method is conducted to analyze the coupled internal-external flow and heat transfer within the inlet anti-icing cavity. Dimensionless characteristic parameters are established for evaluating the swirl nozzle anti-icing system performance. The influence of Nozzle Jet Angle （NJA）， Nozzle Position （NP）， and Nozzle Area Ratio （NAR） on surface temperature distribution and uniformity at the inlet lip are investigated. The regular relationship formula between the average Reynolds number and the Nusselt number was obtained for swirl nozzle anti-icing flow and heat transfer. Results show that： Increasing the hot air jet distance enhances the swirl nozzle anti-icing system performance； changing NJA and NP slightly offset toward the internal flow channel side of the inlet significantly improves temperature uniformity of the lip. Increasing the area of the orifice which is adjacent to the inlet， improves temperature uniformity of the lip but simultaneously raises the risk of overheating of the inlet lip.

Key words: engine inlet, swirl nozzle, anti-icing system, heat transfer characteristics, impinging jet, annular flow

CLC Number:

V211.48

Jinge YIN, Lijuan FENG, Yang DENG. Heat transfer characteristics of engine inlet swirl nozzle anti-icing system[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(11): 633004.

Figures/Tables 24

Fig.1

Fig.2

Fig.3

Fig.4

Table 1

Fig.5

Fig.6

Fig.7

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

Fig.13

Table 2

Temperature characteristic parameters at lip for different NJAs

序号	NJA/（°）	$T m a x'$	$T m i n'$	$T a v e'$	$C t e m d e v$
1	16	0.478 2	0.283 6	0.341 3	10.6%
2	12	0.428 9	0.279 6	0.337 8	9.61%
3	6	0.421 0	0.283 4	0.336 3	8.24%
4	0	0.429 2	0.281 4	0.333 1	8.31%
5	-2	0.435 5	0.282 9	0.334 4	8.3%
6	-6	0.445 9	0.283 0	0.334 4	8.63%
7	-12	0.476 5	0.282 6	0.335 8	9.64%
8	-16	0.498 2	0.277 6	0.335 9	11.28%

Table 2

Fig.14

Fig.15

Fig.16

Table 3

Temperature characteristic parameters at lip for different NPs

序号	NP/mm	$T m a x'$	$T m i n'$	$T a v e'$	$C t e m d e v$
1	70	0.423 2	0.281 4	0.338 3	8.96%
2	50	0.424 6	0.283 5	0.335 6	8.49%
3	30	0.431 2	0.268 8	0.334 6	8.55%
4	10	0.420 1	0.261 3	0.335 5	8.47%
5	0	0.422 8	0.262 6	0.331 8	8.87%
6	-10	0.441 3	0.257 1	0.329 9	9.12%
7	-30	0.463 1	0.250 4	0.328 0	10.84%
8	-50	0.512 6	0.238 7	0.323 1	14.05%

Table 3

Fig.17

Fig.18

Fig.19

Table 4

Temperature characteristic parameters at lip for different NARs

序号	NAR	$T m a x'$	$T m i n'$	$T a v e'$	$C t e m d e v$
1	0.2/0.4/0.4	0.457 8	0.276 5	0.339 9	10.53%
2	0.4/0.2/0.4	0.463 3	0.281 0	0.339 1	10.16%
3	0.4/0.4/0.2	0.484 9	0.283 9	0.338 5	10.19%

Table 4

Fig.20

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类型	参数	数值
飞行状态	H/m	6 000
	Ma	0.427
	T_∞/K	263.55
引气	P_tot/Pa	350 000
	T_tot/K	645
	m_nozzle/（kg·s^-1）	0.5

Heat transfer characteristics of engine inlet swirl nozzle anti-icing system

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