JT8D
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JT8D
JT8D
Pratt & Whitney JT8D-17A 1.JPG
The JT8D is a low-bypass turbofan often used on early narrowbody jetliners
Type Turbofan
United States
Manufacturer Pratt & Whitney
First run 1960
Boeing 727
Boeing 737-100/-200
McDonnell Douglas DC-9
McDonnell Douglas MD-80
14,750 [1]
Pratt & Whitney J52
Volvo RM8

The Pratt & Whitney JT8D is a low-bypass (0.96 to 1) turbofan engine introduced by Pratt & Whitney in February 1963 with the inaugural flight of the Boeing 727. It was a modification of the Pratt & Whitney J52 turbojet engine which powered the US Navy A-6 Intruder attack aircraft. The Volvo RM8 is an afterburning version that was license-built in Sweden for the Saab 37 Viggen fighter. Pratt & Whitney also sells static versions for powerplant and ship propulsion as the FT8.

Design

Cutaway showing the configuration : twin fan, axial compressor stages, canular combustors and 4-stage turbine

The JT8D is an axial-flow front turbofan engine incorporating dual-spool design. There are two coaxially-mounted independent rotating assemblies: one rotating assembly for the low pressure compressor (LPC) which consists of the first six stages (i.e. six pairs of rotating and stator blades, including the first two stages which are for the bypass turbofan), driven by the second (downstream) turbine (which consists of three stages); and a second rotating assembly for the high-pressure compressor (HPC) section, which has seven stages. The high-pressure compressor is driven by the first (upstream) turbine, which has a single stage.

The front-mounted bypass fan has two stages. The annular discharge duct for the bypass fan runs along the full length of the engine, so that both the fan air and exhaust gases can exit through the same nozzle. This arrangement allows some noise attenuation, in that the still-hot fast-moving turbine exhaust is shrouded in much-cooler and slower-moving air (from the bypass fan) before interacting with ambient air. Thus the JT8D noise levels were significantly reduced from previous non-turbofan engines, although the low bypass ratio meant that, compared to subsequently developed turbofans, high noise levels were still produced.

Eight models comprise the JT8D standard engine family, covering the thrust range from 12,250 to 17,400 pounds-force (62 to 77 kN) and power 727, 737-100/200, and DC-9 aircraft. More than 14,000 JT8D engines have been produced, totaling more than one-half billion hours of service with more than 350 operators making it the most popular of all low-bypass turbofan engines ever produced.

Within the fan inlet case, there are anti-icing air bosses and probes to sense the inlet pressure and temperature. Similar units exist throughout the engine to check temperatures and pressures.

At the 13th (i.e. the final) compressor stage, air is bled out and used for anti-icing. The amount is controlled by the Pressure Ratio Bleed Control sense signal (PRBC). The diffuser case at the aft end of the compressor houses the 13th stage. Its increasing cross-sectional area allows the compressed air to slow down before entering one of the engine's nine burner cans. Again, there are two bosses to extract 13th stage air for anti-icing, de-icing of fuel, and airframe (cabin pressurization) use. Not all the compressed air enters the burner cans at the fuel-ignition point; some bypasses the can completely and cools the first turbine stage, and some is gradually introduced into the burner can's perimeter in such a way that the burning fuel is held near the can's centerline.

There are nine combustion chambers positioned in a can-annular arrangement. Each chamber has three air inlet hole sizes: the smallest is for cooling, the medium is for burning and the large for forming an air blanket.

Update programs

Testing at the Glenn Research Center in 1974

In response to environmental concerns that began in the 1970s, the company began developing a new version of the engine, the JT8D-200 series.[2] Designed to be quieter, cleaner, more efficient, yet more powerful than earlier models, the -200 Series power-plant was re-engineered with a significantly higher bypass ratio (1.74 to 1) covering the 18,500 to 21,700 pound-force (82 to 97 kN) thrust range and powering the McDonnell Douglas MD-80 series. This increase was achieved by increasing bypass fan diameter from 39.9 inches (101 cm) to 49.2 inches (125 cm) and reducing fan pressure ratio (from 2.21 to 1.92).[] Overall engine pressure ratio was also increased from 15.4 to 21.0.[3] Since entering service in 1980, more than 2,900 of the -200 series engines have been produced.

The JT8D-217 and -219 engine(s) were tested in 2001 and were deemed suitable replacements for the old TF33 engines on military and commercial aircraft as part of the Super 27 re-engining program. The updated engines offer reduced (Stage-3) noise compliance standards without the need for hush kits, enhanced short field performance, steeper and faster climb rates with roughly a 10% reduction in fuel burn for extended range.

Pratt & Whitney, in a joint venture with Seven Q Seven (SQS) and Omega Air, has developed the JT8D-219 as a re-engine powerplant for Boeing 707-based aircraft.[4] Northrop Grumman used the -219 to re-engine one of the United States Air Force's fleet of 19 Joint Surveillance Target Attack Radar System (E-8 Joint STARS) aircraft, which would allow the JSTARS more time on station due to the engine's 17% [5] greater fuel efficiency. NATO plans to re-engine their fleet of E-3 Sentry AWACS aircraft. The -219 is publicized as being half the cost of the competing 707 re-engine powerplant, the CFM International CFM56, for reasons of geometrical and balance similarity to the engine it is replacing and the associated relative up-front wing modification costs of the two choices.[4][5]

The proposed Aerion SBJ supersonic business jet, previously under development, was to use a pair of JT8D-219 engines for sustained supersonic flight.

Variants

JT8D-219 on the Omega Air Boeing 707RE flight test aircraft at the Mojave Airport
Series Initial variants[6] Updated -200 series[7]
Model -1(A/B)/7(A/B)
/9(A)/11
-5 -15(A) -17(A/R/AR) -209 -217(A/C) -219
Certification Feb 1, 1963 Apr 7, 1971 Feb 1, 1974 Jun 22, 1979 Oct 31, 1980 Feb 22, 1985
Compressor axial 13-stage axial 14-stage
Combustors, turbine 9 can-annular, 4-stage
Maximum Thrust 12,600 lbf
56 kN
12,250 lbf
54.5 kN
13,750 lbf
61.2 kN
15,200 lbf
68 kN
16,000 lbf
71 kN
18,000 lbf
80 kN
18,900 lbf
84 kN
Length 123.56 in (3,138 mm) 154.20 in (3,917 mm)
Width 42.50 in (1,080 mm) 59.20 in (1,504 mm)
Height 53.45 in (1,358 mm) 67.30 in (1,709 mm)
Dry Weight 3,205-3,402 lb
1,454-1,543 kg
3,205 lb
1,454 kg
3,414-3,474 lb
1,549-1,576 kg
3,430-3,500 lb
1,560-1,590 kg
4,588 lb
2,081 kg
4,623-4,684 lb
2,097-2,125 kg
4,684 lb
2,125 kg
LP rpm 8,600 8,500 8,800 8,800-8,900 7,850 7,770-8,080 8,120
HP rpm 12,250 12,100 12,250 12,250-12,280 12,150 12,285-12,350 12,350

Applications

Accidents

18 January 1969
United Airlines Flight 266 - Ten minutes after takeoff, the cockpit received a warning from Engine 1 of an engine fire and cut off power to that engine. A minute later, Flight UA266 suffered a total loss of electrical power, which disabled the aircraft's flight instruments. At 13 minutes post-take off, the plane crashed into the Pacific Ocean, just 12 miles off the coast, killing all 38 people aboard the aircraft, which consisted of 32 passengers and six crew members.
4 April 1977
Southern Airways Flight 242 - both engines on the DC-9 failed when the pilots flew into a severe thunderstorm after misreading their onboard radar. The flight encountered severe rain and hail. The NTSB concluded that the "loss of thrust was caused by the ingestion of massive amounts of water and hail which in combination with thrust lever movement induced severe stalling in and major damage to the engine compressors." Some 63 people on-board and nine on the ground died as a result of the accident.
22 August 1985
British Airtours Flight 28M - an engine failed during take-off from Manchester Airport and a fire spread into the cabin, resulting in 55 fatalities aboard the Boeing 737-236 Advanced.
9 September 1985
Midwest Express Flight 105 - NTSB concluded that an unconfined failure of the 9th - 10th stage compressor spacer occurred immediately after takeoff from Milwaukee Mitchell International Airport (then called Billy Mitchell Field). The plane was observed to have slowed significantly as a result of the engine loss and experienced an accelerated stall condition. The plane rolled to the right 90 degrees and crashed just south of the runway, resulting in 31 fatalities (all passengers and crew) aboard the McDonnell-Douglass DC-9 aircraft.[9]
3 May 1991
Ryan Airlines - Unconfined failure of 9th stage compressor disc penetrated fuel lines and fuselage on the tarmac at Bradley International Airport causing fire and complete loss of aircraft. No fatalities reported.[10]
21 December 1991
Scandinavian Airlines Flight 751 - The engines on an MD-81 ingested wing ice during takeoff causing engine damage that led to a total loss of thrust on both engines. The aircraft crashed in a forest clearing with no fatalities.
6 July 1996
An engine explosion happened on an MD-88, Delta Air Lines Flight 1288, just prior to take-off at Pensacola, Florida, USA, with two fatalities.
15 April 2008
A DC-9-51 operated by Hewa Bora Airways crashed and burned at Goma following an engine fire, with 40 fatalities.
10 July 2019
A McDonnell Douglas MD-88 operated by Delta landed safely after an engine failure.[11]

Specifications (JT8D-219)

Data from PW[12]

General characteristics

Components

Performance

See also

Related development

Comparable engines

Related lists

References

  1. ^ https://pw.utc.com/en/products-and-services/products/commercial-engines/jt8d JT8D ENGINE
  2. ^ Gunston, Bill (1999). The Development of Piston Aero Engines, 2nd Edition. Sparkford, Somerset, England, UK: Patrick Stephens, Haynes Publishing. p. 169. ISBN 0-7509-4478-1.
  3. ^ Pratt & Whitney website, accessed 14 October 2007
  4. ^ a b Flug Revue, May 12, 2002 Archived November 7, 2007, at the Wayback Machine
  5. ^ a b Re-engining the E-8 JSTARS, May 14, 2008
  6. ^ "Type Certificate E2EA data sheet" (PDF). Federal Aviation Administration. August 28, 2007.
  7. ^ "Type Certificate E9NE data sheet" (PDF). Federal Aviation Administration. December 13, 2010.
  8. ^ Pratt & Whitney Celebrates Completion of 50th FT8 MobilePac Power Generator: Hartford Courant, July 18, 2011
  9. ^ https://www.ntsb.gov/investigations/AccidentReports/Reports/AAR8701.pdf | NTSB Aircraft Accident Report AAR8701
  10. ^ "ASN Aircraft accident Boeing 727-22QC N425EX Hartford-Bradley International Airport, CT (BDL)". Aviation Safety Network.
  11. ^ https://www.cnn.com/2019/07/09/us/delta-flight-engine-damage-video/index.html
  12. ^ "JT8D-219Turbofan Engine" (PDF). Pratt & Whitney. September 2010. Archived from the original (PDF) on 2017-05-10. Retrieved .

External links


  This article uses material from the Wikipedia page available here. It is released under the Creative Commons Attribution-Share-Alike License 3.0.

JT8D
 



 



 
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