#
Aerodynamic design framework for low-pressure compression systems
Doktorsavhandling, 2018

manufacturing variations

optimization

stage matching

tip clearance

validation

Turbomachinery

CFD

surface roughness

compressor

## Författare

### Marcus Lejon

Chalmers, Mekanik och maritima vetenskaper, Strömningslära

### Lejon, M., Mårtensson, H., Andersson, N., Ellbrant, L. The Impact of Manufacturing Variations on Performance of a Transonic Axial Compressor Rotor,

### Multidisciplinary Design of a Three Stage High Speed Booster

ASME Turbo Expo 2017: Turbine Technical Conference and Exposition,; (2017)

**Paper i proceeding**

### On Improving the Surge Margin of a Tip-Critical Axial Compressor Rotor

ASME Turbo Expo 2017: Turbine Technical Conference and Exposition,; (2017)

**Paper i proceeding**

### The Surge Margin of an Axial Compressor: Estimations from Steady State Simulations

ISABE International Society for Air Breathing Engines,; (2017)p. 1-13

**Konferensbidrag (offentliggjort, men ej förlagsutgivet)**

### Optimization of Robust Transonic Compressor Blades

ASME Turbo Expo 2016: Turbine Technical Conference and Exposition,; Vol. 2C(2016)

**Paper i proceeding**

### Simulation of Tip-Clearance Effects in a Transonic Compressor

ASME Turbo Expo 2015: Turbine Technical Conference and Exposition,; (2015)

**Paper i proceeding**

### CFD Optimization of a Transonic Compressor Stage with a Large Tip Gap

ISABE International Society for Air Breathing Engines,; (2015)p. 1-11

**Konferensbidrag (offentliggjort, men ej förlagsutgivet)**

To achieve a low fuel consumption, modern turbofan engines operate at high pressure ratios achieved in part by the low-pressure system, consisting of the fan and an axial compressor. An axial compressor consists of a set of consecutive stages, each consisting of a rotating and stationary blade row. While a compressor should operate with a high pressure ratio, it should not operate too close to its stability limit where surge can occur. If surge occur in the compressor, the blades will be subject to large transient forces and the flow may even reverse direction. This work has focused on improving a design framework for designing blades in a low-pressure compression system with a high efficiency and stability. A number of compressor stages and a fan blade are considered as part of the present work, where an appropriate level of modeling complexity is determined and performance is estimated from computational fluid dynamics (CFD) calculations. Criteria that can be used to rank compressor stages in terms of stability in an optimization are investigated, and a conclusion is presented regarding an appropriate measure.

Furthermore, the impact of geometric variations from manufacturing on performance is studied, a topic which is growing in popularity. If too much variability is allowed, it can have an adverse impact on efficiency and may even be a cause for concern from a safety perspective. However, if the allowed variability is set too strict, variations which are not detrimental to performance may need to be corrected at a high cost.

### Ämneskategorier

Produktionsteknik, arbetsvetenskap och ergonomi

Rymd- och flygteknik

Farkostteknik

### Drivkrafter

Hållbar utveckling

### Styrkeområden

Transport

Energi

### Infrastruktur

C3SE (Chalmers Centre for Computational Science and Engineering)

### ISBN

978-91-7597-759-1

Doktorsavhandlingar vid Chalmers tekniska högskola. Ny serie: 4440

### Utgivare

Chalmers tekniska högskola

HA2

Opponent: Heinz-Peter Schiffer, Technische Universität Darmstadt, Germany