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Composite turbine blade and turbine rotor assembly including same

A technology of turbine blades and composite materials, which is applied to the support elements of blades, engine elements, machines/engines, etc., and can solve problems such as damage, failure of composite turbine blades, and stress concentration of composite turbine blades.

Active Publication Date: 2015-07-29
ROLLS ROYCE PLC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Failure of the adhesive bond between the protective strip and the leading edge of the airfoil portion of the composite turbine blade would mean that the composite turbine blade would not meet certification requirements when subjected to certain loads
Furthermore, tip loads from the protective strips on the leading edge of the airfoil portion of the turbine blade can cause stress concentrations within the composite turbine blade, which can lead to failure or damage to the composite turbine blade

Method used

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  • Composite turbine blade and turbine rotor assembly including same
  • Composite turbine blade and turbine rotor assembly including same
  • Composite turbine blade and turbine rotor assembly including same

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0026] like figure 1 The illustrated fan turbine gas turbine engine 10 includes, in flow sequence, an intake 11, a fan 12, an intermediate pressure compressor 13, a high pressure compressor 14, a combustor 15, a high pressure turbine 16, an intermediate pressure turbine 17, a low pressure turbine 18, and an exhaust gas turbine. Air port 19. The high pressure turbine 16 is arranged to drive the high pressure compressor 14 via a first shaft 26 . The medium pressure turbine 17 is arranged to drive the medium pressure compressor 13 via the second shaft 28 and the low pressure turbine 19 is arranged to drive the fan 12 via the third shaft 30 . During operation, air flows into the air inlet 11 and is compressed by the fan 12 . A first part of the air flows through and is compressed by the medium-pressure compressor 13 and the high-pressure compressor 14 and is supplied to the combustion chamber 15 . Fuel is injected into combustion chamber 15 and combusted in the air to produce h...

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PUM

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Abstract

A composite turbomachine blade (34) comprises a composite material including reinforcing fibres in a matrix material, the turbomachine blade (34) comprises an aerofoil portion (36), a shank portion (38) and a root portion (40). The aerofoil portion (36) has a leading edge (42), a trailing edge (44). The composite turbomachine blade (34) also has a metallic protective member (52) arranged in the region of the leading edge (42) of the aerofoil portion (36) of the turbomachine blade (34). The metallic protective member (52) is adhesively bonded to the composite material in the region of the leading edge (42) of the aerofoil portion (36) of the composite turbomachine blade (34). The metallic protective member (52) has at least one metallic projection (56, 58) extending from the metallic protective member (52) towards the root portion (40) of the composite turbomachine blade (34). The at least one metallic projection (56, 58) reduces local peak stress levels and increases high cycle fatigue strength in the composite material, the adhesive and the metallic protective member.

Description

technical field [0001] The present invention relates to composite turbine blades and in particular to composite gas turbine engine blades such as composite fan blades. Background technique [0002] Composite turbine blades are provided with a protective strip on the leading edge of the airfoil portion of the turbine blade in order to protect the leading edge from erosion due to small foreign objects such as sand and to protect the leading edge from large foreign objects (e.g. bird) strikes. [0003] The protective strip is usually a metallic protective strip. The protective sheet is typically adhesively bonded to the leading edge of the airfoil portion of the composite turbine blade. However, the spalling stresses at the radially inner ends of the protective strips have not been optimized, resulting in the loss of the protective strips and composite turbine blades under certain loading conditions, for example due to the impact of one or more birds. Early failure of the ad...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/12F01D5/30
CPCF04D29/324F01D5/282F05D2240/303F05D2260/941
Inventor D.I.詹姆斯N.M.梅里曼
Owner ROLLS ROYCE PLC