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Improving acceleration of gas turbine

A technology of gas turbine and turbine, which is applied in the direction of fuel control of turbine/propulsion device, gas turbine device, turbine/propulsion fuel delivery system, etc., and can solve problems such as seldom referring to the optimal control strategy

Pending Publication Date: 2020-12-15
ROLLS ROYCE PLC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

While many literatures present candidates for optimal physical implementations of such architectures, there is little reference to optimal control strategies to operate such configurations

Method used

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  • Improving acceleration of gas turbine
  • Improving acceleration of gas turbine
  • Improving acceleration of gas turbine

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Embodiment Construction

[0033] The invention is described in the context of a two-spool geared turbofan engine architecture. However, it will be apparent to those skilled in the art that the principles of the present invention can be applied to other engine types, including gas turbines having two or more slide valves, such as direct drive turbofans, turboprops, or open rotor engines .

[0034] figure 1 and figure 2

[0035] The general arrangement structure of the engine 101 of aircraft is in figure 1 is shown in the equivalent block diagram of its main components in figure 2 shown in .

[0036] In this embodiment, the engine 101 is a turbofan and thus includes a ducted fan 102 which receives intake air A and generates two streams: a bypass flow B axially through a bypass duct 103 and a flow B into the core gas turbine. core flow C.

[0037] The core gas turbine includes a low pressure compressor 104 , a high pressure compressor 105 , a combustor 106 , a high pressure turbine 107 and a l...

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PUM

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Abstract

The title of the invention is improving acceleration of a gas turbine. The invention discloses a gas turbine engine (101) for an aircraft, and the gas turbine engine (101) comprises a high-pressure (HP) spool comprising an HP compressor (105) and a first electric machine (117) driven by an HP turbine (107); a low-pressure (LP) spool comprising an LP compressor (104) and a second electric machine (119) driven by an LP turbine (108); a combustion system (106) comprising a fuel metering unit; and an engine controller (123) configured to, in response to a change of a throttle lever angle setting indicative of an acceleration event, increase fuel flow to the combustion system (106) by the fuel metering unit, and to operate the first electric machine (117) in a motor mode to increase the HP spool rotational speed and engine core mass flow.

Description

technical field [0001] The present disclosure relates to gas turbine engines. Background technique [0002] Gas turbine engines having electric machines capable of operating both as motors and generators are known, such as those used in more electric aircraft. While such engines may include multiple such motors for redundancy, they are coupled to only one of the spool valves. For example, one known configuration includes such a motor coupled to a high pressure spool valve of a dual spool turbofan. Another configuration includes such a motor coupled to the medium pressure spool of a three spool turbofan. [0003] The problem with such a configuration is that, for a given electrical power demand, there is no choice but to provide electrical power from a single spool valve in the engine. Therefore, the turbomachinery must be designed to accommodate all possible electrical power demands over the entire operating range, which inevitably leads to trade-offs. [0004] Therefore...

Claims

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Application Information

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IPC IPC(8): F02C3/06F02C3/08F02C6/00F02C9/26B64D15/00F02K3/06
CPCF02C3/06F02C3/08F02C6/00F02C9/26B64D15/00F02K3/06F02C7/32F01D15/10F05D2270/044F02C9/56F02C7/36F05D2220/76Y02T50/60F02C9/16F02C9/28F02C9/285F02C9/44F02C9/48F02C9/50F05D2270/02F05D2270/023F05D2270/10F05D2270/20F05D2270/304F05D2270/3061H02K7/1823F05D2220/323F05D2270/04
Inventor 保罗·D·惠特利
Owner ROLLS ROYCE PLC
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