40:
174:
An unusual addition to the R-25 was an emergency mode thrust boost which increased the compressor speed to 106% and also increased the afterburner fuel flow with the addition of a second afterburner fuel pump. Thrust was increased to 96.5 kilonewtons
179:) below an altitude of 2,000 metres (6,600 ft). The time limit for its use was 1 minute during training and 2 minutes in wartime, as further use caused the engine to overheat and be irreparably damaged. Use of this
183:
required the engine to be removed on landing for inspection. Use of WEP shortened the already limited time between overhaul typical of Soviet-made engines of that era compared to
Western engines.
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194:. A total of 3,200 R-25 were built between 1971 and 1975. The engine was also built under license by HAL in
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and airflow, variable two-stage afterburner, and greater use of
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349:
340 kg/(h·kN) (3.34 lb/(h·lbf)) max afterburner emergency
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98 kg/(h·kN) (0.96 lb/(h·lbf)) at maximum military power
147:
The
Tumansky R-25 was designed as a replacement for the
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engine, which is seen as the ultimate development of
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488:
346:229 kg/(h·kN) (2.25 lb/(h·lbf)) max afterburner
463:
8:
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135:. It was designed under the leadership of
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340:93 kg/(h·kN) (0.91 lb/(h·lbf)) at idle
29:
49:Karhulan ilmailukerho Aviation Museum
27:1970s Soviet turbojet aircraft engine
7:
155:fighters. The R-25 is a two-spool
25:
309:97.1 kilonewtons (21,800 lb
302:69.6 kilonewtons (15,600 lb
186:The R-25 engine was used on the
38:
295:40.3 kilonewtons (9,100 lb
1:
47:Tumanski R-25-300 engine in
313:) max afterburner emergency
137:Sergei Alekseevich Gavrilov
613:
326:Turbine inlet temperature:
592:Tumansky aircraft engines
425:"R-25 (LeteckeMotory.cz)"
411:"R-25 (LeteckeMotory.cz)"
333:Specific fuel consumption
206:Specifications (R-25-300)
46:
37:
32:
442:R-25 on LeteckeMotory.cz
391:List of aircraft engines
257:3 LP stages, 5 HP stages
211:General characteristics
94:Mikoyan-Gurevich MiG-21
597:1970s turbojet engines
354:Thrust-to-weight ratio
318:Overall pressure ratio
275:1 HP stage, 1 LP stage
165:overall pressure ratio
143:Design and development
358:5.6 (max afterburner)
159:turbojet with a new
368:Related development
328:1,040 °C (1,904 °F)
266:Cannular 10 burners
240:1,212 kg (2,670 lb)
228:4,615 mm (181.7 in)
234:1,191 mm (46.9 in)
85:Major applications
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578:
306:) max afterburner
198:for its fleet of
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71:, UMPO NPP Motor
18:Tumansky R-25-300
16:(Redirected from
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482:aircraft engines
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255:axial compressor
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192:Sukhoi Su-15bis
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175:(21,700 lb
163:with increased
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490:Piston engines
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436:External links
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111:Developed from
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385:Related lists
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379:Tumansky R-13
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374:Tumansky R-11
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219:Afterburning
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149:Tumansky R-13
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133:Tumansky R-11
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125:Tumansky R-25
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116:Tumansky R-11
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65:Manufacturer
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528:Gas turbines
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101:Number built
90:Sukhoi Su-15
280:Performance
251:Compressor:
238:Dry weight:
586:Categories
397:References
262:Combustors
253:Two-spool
245:Components
161:compressor
157:axial-flow
76:First run
232:Diameter:
200:MiG-21bis
188:MiG-21bis
479:Tumansky
363:See also
286:Maximum
221:turbojet
190:and the
169:titanium
129:turbojet
69:Tumansky
59:Turbojet
271:Turbine
226:Length:
288:thrust
153:MiG-21
105:3,200
541:RD-10
322:9.5:1
217:Type:
196:India
127:is a
79:1971
55:Type
33:R-25
571:R-29
566:R-25
561:R-21
556:R-15
551:R-13
546:R-11
536:RD-9
518:M-90
513:M-88
508:M-87
503:M-86
498:M-85
444:(cs)
123:The
181:WEP
151:in
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299:)
202:.
171:.
139:.
471:e
464:t
457:v
427:.
413:.
356::
335::
320::
311:f
304:f
297:f
290::
273::
264::
177:f
20:)
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