Rolls-Royce BR700

From Wikipedia, the free encyclopedia
Jump to: navigation, search
BR700 series
Engine BR710-1.jpg
Rear view of a BR710
Type Turbofan
Manufacturer BMW Rolls-Royce
Rolls-Royce Deutschland
First run 1994
Major applications Bombardier Global Express
Boeing 717
Gulfstream V

The Rolls-Royce BR700 family of engines powering regional jets and corporate jets. It was developed by BMW and Rolls-Royce plc through the joint venture BMW Rolls-Royce AeroEngines GmbH, established in 1990. The engine first ran in September 1994 (a BR710) and is manufactured in Dahlewitz, Germany. Rolls-Royce took full control of the company in 2000, which is now known as Rolls-Royce Deutschland.

Design and development[edit]


A G550 in front of a Global Express : the BR710 main applications

The BR710 is a twin shaft turbofan, entered service on the Gulfstream V in 1997 and the Bombardier Global Express in 1998. This version has also been selected to power the Gulfstream G550.

Another rerated version, with a revised exhaust system, was selected for the now cancelled Royal Air Force Nimrod MRA4s.

The BR710 comprises a 48-inch-diameter single-stage fan, driven by a two-stage LP turbine, supercharging a ten-stage HP compressor (scaled from the V2500 unit) and driven by a two-stage, air-cooled, HP turbine.


A BR715 engine on a Midwest Airlines Boeing 717

The BR715 is another twin-shaft turbofan; this engine was first run in April 1997 and entered service in mid-1999. This version powers the Boeing 717.

A new LP spool, comprising a 58-inch-diameter single-stage fan, with two-stage LP compressor driven by a three-stage LP turbine, is incorporated into the BR715. The HP spool is similar to that of the BR710.

The IP compressor booster stages supercharge the core, increasing core power and thereby net thrust. However, a larger fan is required, to keep the specific thrust low enough to satisfy jet noise considerations.


The BR725 powers the Gulfstream G650

The BR725 is a variant of the BR710 with a three-stage-axial flow low pressure turbine to power the Gulfstream G650.[1] The engine has a maximum thrust of 17,000 pounds-force (75.6 kN).[2]

The BR725 has a bypass ratio of 4.2:1, and is 4 dB quieter than the predecessor BR710. Its 50-inch (127 cm) fan assembly consists of 24 swept titanium blades.

The BR725 prototype underwent component bench and its first full engine run in spring 2008[3] and European certification was achieved in June 2009.[4] The first Gulfstream G650, with BR725 engines, was delivered in December 2011.[5]


Advance 2 development effort inserts new, advanced technology into existing 15,000-lb class BR710 and larger BR725 and a larger member will be added with a 52-inch fan. BR710 and BR715 main developments, the next generation of 10,0000 to 20,000 lbf engines to be introduced in the 2020s will have an Advance 3 core, improved engine health management, newer materials and cooling, a titanium “blisked” fan and an overall pressure ratio of 50:1 for a 10% thrust specific fuel consumption reduction, 50% NOx margin improvement, 99.995% reliability and a 20% better thrust-to-weight ratio.[6]


Variant with a 65.6kN takeoff rating and a maximum diameter of 1820mm.[7]
Variant with a 65.6 kN (14,700 lbf) takeoff rating and a maximum diameter of 1820mm.[7]
Variant with a 69 kN (16,000 lbf) takeoff rating for the BAE Systems Nimrod MRA4.[8]
Variant with a 68.4kN takeoff rating and a maximum diameter of 1785mm.[7]
Variant with an 83.23kN (18,500 lbf) takeoff rating for Boeing 717-200 basic gross weight variants.[9]
Variant with an 89.68kN (20,000 lbf) takeoff rating.[9]
Variant with a 95.33kN (21,000) takeoff rating for Boeing 717-200 high gross weight variants.[9]
Variant with a 71.6 kN (16,100 lbf) takeoff rating.[7]

The BR715 thrust ratings can be adjusted by changing a plug in the FADEC controller, meaning no engine change is required. The A1-30 can become a C1-30 with a simple plug and software change.



BR700 family specifications
Model BR710-48 BR715-58 BR725-50
Thrust (lb) 14,750–15,500 lbf (65.6–68.9 kN) 18,500–22,000 lbf (82.3–97.9 kN) 15,000–17,000 lbf (66.7–75.6 kN)
Dry Weight (lb) 4,640 lb (2,100 kg) 6,155 lb (2,792 kg) 4,912 lb (2,228 kg) appx
Overall Length (in) 134 in (3.4 m) 147 in (3.7 m) 202 in (5.1 m) nacelle
Fan Diameter (in) 48 in (1.2 m) 58 in (1.5 m) 50 in (1.3 m)

See also[edit]

Comparable engines
Related lists


External links[edit]