General Electric F101-GE-102

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About the F101-GE-102 Engine:





The General Electric F101 is an afterburning turbofan engine developed for the Advanced Manned Strategic Aircraft program, which later became the B-1A strategic bomber. The F101 is in the 30,000 pound thrust class and was General Electric's first turbofan engine with an augmentor. The planned production program was terminated in 1977 and only four B-1 strategic bombers were built.

Later, General Electric were awarded a contract to develop the F101-GE-102 augmented turbofan for the Rockwell (now Boeing) B-1B Lancer. It is an improved version from the earlier flight test engine used on the first B-1s. The first F-101-GE-102 engine was delivered in 1983 and B-1B flight testing began the following year. The U.S. Air Force received the first B-1B Lancer in 1985 and the last of a total of 469 F101-GE-102 engines manufactured left the production line in December 1987.

The Boeing B-1B Lancer is the backbone of the U.S. long-range bomber force. It can rapidly deliver massive quantities of precision and non-precision weapons against any adversary anywhere in the world at any time.

The General Electric F110 turbofan (used on the F-16 Fighting Falcon) is a derivative of the F101. Furthermore, General Electric used the core of the F101 for the successful F108/CFM56 family of high-bypass turbofan engines.




Source: U.S. Department of Defense (DoD) and General Electric Company

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Engine Type:

Two-Spool Afterburning Turbofan Engine

Applications:

B-1B Lancer

Status:

In Service

Manufacturer:

General Electric Co.

Price/Unit Cost:

Unknown

General Electric F101 Turbofan Engine

Last Update: October 3, 2016.

By Joakim Kasper Oestergaard Balle /// Contact Forecast International

External Resources:



GE Aviation F101 Page: Not Available

YouTube: The F101 on YouTube

Fact Sheet: General Electric F101

Specifications

Engine Specifications: F101-GE-102 Turbofan

Manufacturer: General Electric Co.
Thrust: 30,780 pounds
Overall Pressure Ratio at Maximum Power: 26.8
Thrust-to-Weight Ratio: 7
Compressor: Two spool, axial flow, single-stage fan
LP-HP Compressor Stages: 1-9
HP-LP Turbine Stages: 1-2
Combustor: Annular
Length: 181 in (4.59 m)
Diameter: 55 in (140 cm)
Dry Weight: 4,400 lbs (1,996 kg)
Platforms: B-1B Lancer
Price/Unit Cost: Unknown
First Run: Unknown
First Flight: December 23, 1974

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