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US 9,309,769 B2Granted
Gas turbine engine airfoil shaped component
AssigneeROLLS-ROYCE plc
InventorBronwyn Power
Life of this patent
Estimating the term…
Abstract
A gas turbine engine airfoil shaped component is disclosed including in one form a compressor blade or vane having a tip portion capable of producing a relatively low pressure near the leading edge of the tip to induce a local jet of stream-wise momentum flow. In one form the tip portion includes a camber angle distribution that produces relatively large change in camber angle near the leading edge but relatively flat distribution for remainder of blade. In one form the tip portion includes relatively large change in camber angle near trailing edge.
Claims20
An apparatus comprising:
- a compressor blade of a gas turbine engine capable of being rotated to produce a pressure rise in a working fluid during operation of the gas turbine engine, the compressor blade including a main blade portion having a first camber shape that is blended with a tip portion having a second camber shape, the second camber shape producing a relatively low pressure near the leading edge of the tip to induce a local jet of stream-wise momentum flow,
- wherein the second camber shape is blended into the first camber shape starting at about 2/3 of a height of the compressor blade,
- wherein the second camber shape includes a normalized camber angle defined as
- β
- ′
- =
- β
- i
- -
- β
- β
- i
- -
- β
- e
- where βi is inlet metal angle, βe is exit metal angle, and β is a camber angle at a given chord location, and
- wherein the normalized camber angle reaches at least 0.4 in the first 10% of normalized chord.
14 more elements
An apparatus comprising:
- a compressor blade of a gas turbine engine capable of being rotated to produce a pressure rise in a working fluid during operation of the gas turbine engine, the compressor blade including a main blade portion having a first camber shape that is blended with a tip portion having a second camber shape, the second camber shape producing a relatively low pressure near the leading edge of the tip to induce a local jet of stream-wise momentum flow,
- wherein the second camber shape includes a normalized camber angle defined as
- β
- ′
- =
- β
- i
- -
- β
- β
- i
- -
- β
- e
- where βiis inlet metal angle, βe is exit metal angle, and β is a camber angle at a given chord location;
- and
- wherein normalized camber angle reaches at least 0.4 in the first 10% of normalized chord.
14 more elements
An apparatus comprising:
- a compressor blade of a gas turbine engine capable of being rotated to produce a pressure rise in a working fluid during operation of the gas turbine engine, the compressor blade including a main blade portion having a first camber shape that is blended with a tip portion having a second camber shape, the second camber shape producing a relatively low pressure near the leading edge of the tip to induce a local jet of stream-wise momentum flow,
- wherein the second camber shape provides a cumulative integral according to the relationship
- 0.4
- <
- ∫
- 0
- 1
-
- [
- ∫
- 0
- x
-
- β
- ′
-
- ⅆ
- x
- ]
-
- ⅆ
- x
- ∫
- 0
- 1
-
- β
- ′
-
- ⅆ
- x
- ≤
- 0.5
- where x is chord location,
- β
- ′
- =
- β
- i
- -
- β
- β
- i
- -
- β
- e
- ,
- βi is inlet metal angle, βe is exit metal angle, and β is a camber angle at a given chord location.
45 more elements
Dependencies are inferred from the claim text.