Characteristics of a downstream-mixing CO<sub>2</sub> gasdynamic laser caused by behavior of two supersonic flows in a laser cavity

Takashi Hashimoto; Susumu Nakano; Michio Hachijin; Katsuhiko Komatsu; Yasuharu Mine; Hiroshi Hara

doi:10.1364/AO.32.005936

Applied Optics
Vol. 32,
Issue 30,
pp. 5936-5943
(1993)
•https://doi.org/10.1364/AO.32.005936

Characteristics of a downstream-mixing CO₂ gasdynamic laser caused by behavior of two supersonic flows in a laser cavity

Takashi Hashimoto, Susumu Nakano, Michio Hachijin, Katsuhiko Komatsu, Yasuharu Mine, and Hiroshi Hara

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Takashi Hashimoto, Susumu Nakano, Michio Hachijin, Katsuhiko Komatsu, Yasuharu Mine, and Hiroshi Hara, "Characteristics of a downstream-mixing CO₂ gasdynamic laser caused by behavior of two supersonic flows in a laser cavity," Appl. Opt. 32, 5936-5943 (1993)

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Abstract

A combustion-driven downstream-mixing CO₂ gasdynamic laser (GDL) is developed. When the total mass flow rate is ~ 2 kg/s and the combustion gas temperature is 1750 K, a small-signal gain coefficient of up to 0.6% cm⁻¹ and a laser output power as high as 11 kW are measured. To explain the experimental values, a mixing loss factor was previously introduced into an analytical model incorporating the three-temperature kinetics model. In the present study, a numerial analysis and further experiments are carried out to clarify the mixing behavior of two supersonic flows in the laser cavity. A measuring method for the average static temperature in the laser resonator is adapted, and it is made clear that, with the current state of supersonic nozzle manufacturing technology, two supersonic flows will not mix well.

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Parameter	This Study	Cassady et al.1	Schall et al.2	Hügel et al.3	Yu et al.7
Material	Oxygen-free copper	Aluminum alloy			Zirconium copper
Height (mm) × width (mm)	35 × 525	20 × 280	12 × 35	16 × 150	20 × 132
Donor gas
Throat (mm)	ϕ0.64 × 0.60la	ϕ0.4 × 0.13la	ϕ0.5	ϕ0.75	ϕ0.5
Exit diameter (mm)	ϕ5.54	ϕ3.5	ϕ4.0	ϕ4.0	ϕ4.5
Area ratio	73.8 (51.7)b	76.5 (60)b	64	28.4	81
Profile	MLSF	Conical (10°)c	Conical (10°)c	Conical (15°)c	Conical (10°)c
Number of nozzles	425	318	27	132	114
Laser gas
Throat (mm)	ϕ0.36 × 0.30la	ϕ0.37	—d	—d	ϕ0.3/ϕ0.5
Exit diameter (mm)	ϕ2.4	ϕ2.11	ϕ0.7	ϕ0.7
Area ratio	44.4 (33.9)b	32.5	—d	—d
Profile	Conical (10°)c	Conical (8°)c
Number of nozzles	516	159	16	96	57
Arrangement	Staggered	Close-packed hexagonal	Staggered	Staggered	Staggered
Nozzle spacing (mm)	4.3	2.8	2.8	2.8	4.0
Nozzle length (mm)	61	20

	This Study	Cassady et al.1	Schall et al.2	Hügel et al.3	Yu et al.7
Operation	Combustion driven	Shock tube	Arc heater	Arc heater	Arc heater
Mixing	Supersonic–supersonic	Supersonic–supersonic	Supersonic–sonic	Supersonic–sonic	Supersonic–supersonic
Donor gas
P₀ (MPa)	11.3	6.6	3–6	2–5	0.7
T₀ (K)	1730	2000–2300	2000–3000	1400–4000	2300
Exit Mach number	6	6	3.5–4.5	3.5–4.5	6
Compositiona	3.4 CO₂ + 0.03 H₂O + 73.4 N₂ + 23.0 O₂	N₂	N₂ + Ar	N₂/N₂ + CO/Ar	N₂
Laser gas
P₀ (MPa)	5.0		5–9
T₀ (K)	600	1000	300	300	770
Exit Mach number	5	5	1	1	5/4
Compositiona	98 CO₂ + 2 H₂O	10 CO₂ + 1 H₂O	CO₂ + He	CO₂ + He	CO₂ + He
Laser cavity
Static pressure (kPa)	6.7–8.0			0.3–2.5	0.7–2.0
Mass flow rate (g/s)	1800		7.0	14.4–40.0	20
Compositionb	60.2 N₂ + 19.1 CO₂ + 2.6 H₂O + 20.4 O₂	7–12 CO₂ + 1 H₂O + N₂ balanced	40 N₂ + 7 Ar + 28 CO₂ + 28 He	28 N₂ + 22 CO₂ + 50 He	81 N₂ + 18 CO₂ + 1 H₂O
Small-signal gain (% cm⁻¹)b	0.5	1.0–1.5	1.5–3.0	1.5–3.0	1.0–1.8

Parameter	This Study	Cassady et al.1	Schall et al.2	Hügel et al.3	Yu et al.7
Material	Oxygen-free copper	Aluminum alloy			Zirconium copper
Height (mm) × width (mm)	35 × 525	20 × 280	12 × 35	16 × 150	20 × 132
Donor gas
Throat (mm)	ϕ0.64 × 0.60la	ϕ0.4 × 0.13la	ϕ0.5	ϕ0.75	ϕ0.5
Exit diameter (mm)	ϕ5.54	ϕ3.5	ϕ4.0	ϕ4.0	ϕ4.5
Area ratio	73.8 (51.7)b	76.5 (60)b	64	28.4	81
Profile	MLSF	Conical (10°)c	Conical (10°)c	Conical (15°)c	Conical (10°)c
Number of nozzles	425	318	27	132	114
Laser gas
Throat (mm)	ϕ0.36 × 0.30la	ϕ0.37	—d	—d	ϕ0.3/ϕ0.5
Exit diameter (mm)	ϕ2.4	ϕ2.11	ϕ0.7	ϕ0.7
Area ratio	44.4 (33.9)b	32.5	—d	—d
Profile	Conical (10°)c	Conical (8°)c
Number of nozzles	516	159	16	96	57
Arrangement	Staggered	Close-packed hexagonal	Staggered	Staggered	Staggered
Nozzle spacing (mm)	4.3	2.8	2.8	2.8	4.0
Nozzle length (mm)	61	20

	This Study	Cassady et al.1	Schall et al.2	Hügel et al.3	Yu et al.7
Operation	Combustion driven	Shock tube	Arc heater	Arc heater	Arc heater
Mixing	Supersonic–supersonic	Supersonic–supersonic	Supersonic–sonic	Supersonic–sonic	Supersonic–supersonic
Donor gas
P₀ (MPa)	11.3	6.6	3–6	2–5	0.7
T₀ (K)	1730	2000–2300	2000–3000	1400–4000	2300
Exit Mach number	6	6	3.5–4.5	3.5–4.5	6
Compositiona	3.4 CO₂ + 0.03 H₂O + 73.4 N₂ + 23.0 O₂	N₂	N₂ + Ar	N₂/N₂ + CO/Ar	N₂
Laser gas
P₀ (MPa)	5.0		5–9
T₀ (K)	600	1000	300	300	770
Exit Mach number	5	5	1	1	5/4
Compositiona	98 CO₂ + 2 H₂O	10 CO₂ + 1 H₂O	CO₂ + He	CO₂ + He	CO₂ + He
Laser cavity
Static pressure (kPa)	6.7–8.0			0.3–2.5	0.7–2.0
Mass flow rate (g/s)	1800		7.0	14.4–40.0	20
Compositionb	60.2 N₂ + 19.1 CO₂ + 2.6 H₂O + 20.4 O₂	7–12 CO₂ + 1 H₂O + N₂ balanced	40 N₂ + 7 Ar + 28 CO₂ + 28 He	28 N₂ + 22 CO₂ + 50 He	81 N₂ + 18 CO₂ + 1 H₂O
Small-signal gain (% cm⁻¹)b	0.5	1.0–1.5	1.5–3.0	1.5–3.0	1.0–1.8

Abstract

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Equations (8)

Applied Optics